반응형

 

다음 그림은 세 가지 기체 구성과 형상 변수를 지정할 X 좌표이다. 곡률과 기체 윤곽의 급격한 변화를 정의하는 데 사용된 점을 주목하자. 구성 (c)는 모든 속도 영역에서 기체 단독 분석을 설명하려고 예제 1로 선택되었다. 대략적인 축대칭 기체와 곡선형 기체의 아음속 기체 분석을 수행하였다.

 

기체 모델링 (a) 축대칭 기체, (b) 곡선형 기체, (c) 기체 단독 분석

 

X (FT) S (FT2) P (FT) R (FT) ZU (FT) ZL (FT)
0.0 0.0 0.0 0.0 -0.595 -0.595
0.258 0.080 1.00 0.186 -0.476 -0.715
0.589 0.160 1.42 0.286 -0.372 -0.754
1.26 0.323 2.01 0.424 -0.138 -0.805
2.26 0.751 3.08 0.533 0.200 -0.868
2.59 0.883 3.34 0.533 0.334 -0.868
2.93 0.939 3.44 0.533 0.343 -0.868
3.59 1.032 3.61 0.533 0.343 -0.868
4.57 1.032 3.61 0.533 0.343 -0.868
6.26 1.032 3.61 0.533 0.343 -0.868

 

예제 1에서 4가지 해석의 요약은 다음과 같다.

Case No. Configuration Mach No. Comments
1 Body 0.60 축대칭 해
2 Body 0.60 곡선형 해
3 Body 0.9,1.4,2.5 마하 1.4와 2.5에서 초음속 해석
4 Body 2.5 극초음속 해석

 

이 문제는 CASEID, DUMP CASE, SAVE, 및 NEXT CASE  명령어를 사용하는 방법을 보여준다.

 

입력 파일

 $FLTCON
  NMACH = 1.0,
  MACH(1) = 0.60,
  NALPHA = 11.0,
  ALSCHD(1) = -6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,12.0,16.0,20.0,24.0,
  RNNUB=4.28E6,
 $END
 $OPTINS
  SREF = 8.85,
  CBARR = 2.48,
  BLREF = 4.28,
 $END
 $SYNTHS
  XCG = 4.14,
  ZCG = -0.20,
 $END
 $BODY
  NX = 10.0,
  X(1) = 0.0,0.258,0.589,1.260,2.260,2.590,2.930,3.590,4.570,6.260,
  R(1) = 0.0,0.186,0.286,0.424,0.533,0.533,0.533,0.533,0.533,0.533,
  S(1) = 0.0,0.080,0.160,0.323,0.751,0.883,0.939,1.032,1.032,1.032,
  P(1) = 0.0,1.00,1.42,2.01,3.08,3.34,3.44,3.61,3.61,3.61,
 $END
 $BODY
  BNOSE = 1.0,
  BLN = 2.59,
  BLA = 3.67,
 $END
CASEID APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1
SAVE
DUMP CASE
NEXT CASE
 $BODY ZU(1) = -.595,-.476,-.372,-.138,.200,.334,.343,.343,.343,.343,
       ZL(1) = -.595,-.715,-.754,-.805,-.868,-.868,-.868,-.868,-.868,-.868,
 $END
CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION,EXAMPLE PROBLEM 1,CASE 2
SAVE
NEXT CASE
 $FLTCON
  NMACH = 3.0,
  MACH(1) = 0.9,1.4,2.5,
  RNNUB = 6.4E6,9.96E6,17.0E6,
 $END
SAVE
CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3
NEXT CASE
 $FLTCON
  NMACH = 1.0,
  MACH(1) = 2.5,
  RNNUB = 17.86E6,
  HYPERS = .TRUE.,
 $END
 $BODY
  DS = 0.0,
 $END
CASEID HYPERSONIC BODY SOLUTION,  EXAMPLE PROBLEM 1, CASE 4
NEXT CASE

 

출력 파일

 

  ****************************************************
  *    USAF STABILITY AND CONTROL  DIGITAL DATCOM    *
  *    PROGRAM REV. JAN 96   DIRECT INQUIRIES TO:    *
  *    WRIGHT LABORATORY  (WL/FIGC)  ATTN: W. BLAKE  *
  *      WRIGHT PATTERSON AFB, OHIO  45433           *
  *    PHONE (513) 255-6764,   FAX (513) 258-4054    *
  ****************************************************
1                         CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0******************************  INPUT DATA CARDS  ******************************

  $FLTCON                                                                        
   NMACH = 1.0,                                                                  
   MACH(1) = 0.60,                                                               
   NALPHA = 11.0,                                                                
   ALSCHD(1) = -6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,12.0,16.0,20.0,24.0,               
   RNNUB=4.28E6,                                                                 
  $END                                                                           
  $OPTINS                                                                        
   SREF = 8.85,                                                                  
   CBARR = 2.48,                                                                 
   BLREF = 4.28,                                                                 
  $END                                                                           
  $SYNTHS                                                                        
   XCG = 4.14,                                                                   
   ZCG = -0.20,                                                                  
  $END                                                                           
  $BODY                                                                          
   NX = 10.0,                                                                    
   X(1) = 0.0,0.258,0.589,1.260,2.260,2.590,2.930,3.590,4.570,6.260,             
   R(1) = 0.0,0.186,0.286,0.424,0.533,0.533,0.533,0.533,0.533,0.533,             
   S(1) = 0.0,0.080,0.160,0.323,0.751,0.883,0.939,1.032,1.032,1.032,             
   P(1) = 0.0,1.00,1.42,2.01,3.08,3.34,3.44,3.61,3.61,3.61,                      
  $END                                                                           
  $BODY                                                                          
   BNOSE = 1.0,                                                                  
   BLN = 2.59,                                                                   
   BLA = 3.67,                                                                   
  $END                                                                           
 CASEID APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1        
 SAVE                                                                            
 DUMP CASE                                                                       
 NEXT CASE                                                                       
  $BODY ZU(1) = -.595,-.476,-.372,-.138,.200,.334,.343,.343,.343,.343,           
        ZL(1) = -.595,-.715,-.754,-.805,-.868,-.868,-.868,-.868,-.868,-.868,     
  $END                                                                           
 CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION,EXAMPLE PROBLEM 1,CASE 2             
 SAVE                                                                            
 NEXT CASE                                                                       
  $FLTCON                                                                        
   NMACH = 3.0,                                                                  
   MACH(1) = 0.9,1.4,2.5,                                                        
   RNNUB = 6.4E6,9.96E6,17.0E6,                                                  
  $END                                                                           
 SAVE                                                                            
 CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3           
 NEXT CASE                                                                       
  $FLTCON                                                                        
   NMACH = 1.0,                                                                  
   MACH(1) = 2.5,                                                                
   RNNUB = 17.86E6,                                                              
   HYPERS = .TRUE.,                                                              
  $END                                                                           
  $BODY                                                                          
   DS = 0.0,                                                                     
  $END                                                                           
 CASEID HYPERSONIC BODY SOLUTION,  EXAMPLE PROBLEM 1, CASE 4                     
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON                                                                        
   NMACH = 1.0,                                                                  
   MACH(1) = 0.60,                                                               
   NALPHA = 11.0,                                                                
   ALSCHD(1) = -6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,12.0,16.0,20.0,24.0,               
   RNNUB=4.28E6,                                                                 
  $END                                                                           
  $OPTINS                                                                        
   SREF = 8.85,                                                                  
   CBARR = 2.48,                                                                 
   BLREF = 4.28,                                                                 
  $END                                                                           
  $SYNTHS                                                                        
   XCG = 4.14,                                                                   
   ZCG = -0.20,                                                                  
  $END                                                                           
  $BODY                                                                          
   NX = 10.0,                                                                    
   X(1) = 0.0,0.258,0.589,1.260,2.260,2.590,2.930,3.590,4.570,6.260,             
   R(1) = 0.0,0.186,0.286,0.424,0.533,0.533,0.533,0.533,0.533,0.533,             
   S(1) = 0.0,0.080,0.160,0.323,0.751,0.883,0.939,1.032,1.032,1.032,             
   P(1) = 0.0,1.00,1.42,2.01,3.08,3.34,3.44,3.61,3.61,3.61,                      
  $END                                                                           
  $BODY                                                                          
   BNOSE = 1.0,                                                                  
   BLN = 2.59,                                                                   
   BLA = 3.67,                                                                   
  $END                                                                           
 CASEID APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1        
 SAVE                                                                            
 DUMP CASE                                                                       
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

 
    BD(  1)= 6.26000E+00    BD(  2)= 3.59000E+00    BD(  3)= 1.03200E+00    BD(  4)= 1.03200E+00    BD(  5)= 6.26000E+00
    BD(  6)= 1.03200E+00    BD(  7)= 5.66530E+00    BD(  8)= 1.00000E-30    BD(  9)= 8.43444E-01    BD( 10)= 2.08059E-02
    BD( 11)= 0.00000E+00    BD( 12)= 1.00000E-30    BD( 13)= 1.00000E-30    BD( 14)= 1.00000E-30    BD( 15)= 1.00000E-30
    BD( 16)= 1.00000E-30    BD( 17)= 1.00000E-30    BD( 18)= 1.00000E-30    BD( 19)= 1.00000E-30    BD( 20)= 1.00000E-30
    BD( 21)= 1.00000E-30    BD( 22)= 1.00000E-30    BD( 23)= 1.00000E-30    BD( 24)= 1.00000E-30    BD( 25)= 1.00000E-30
    BD( 26)= 1.00000E-30    BD( 27)= 1.00000E-30    BD( 28)= 1.00000E-30    BD( 29)= 1.00000E-30    BD( 30)= 1.00000E-30
    BD( 31)= 1.00000E-30    BD( 32)= 1.00000E-30    BD( 33)= 4.14000E+00    BD( 34)= 1.00000E-30    BD( 35)= 1.00000E-30
    BD( 36)= 1.00000E-30    BD( 37)= 1.00000E-30    BD( 38)= 1.00000E-30    BD( 39)= 1.00000E-30    BD( 40)= 1.00000E-30
    BD( 41)= 1.00000E-30    BD( 42)= 1.00000E-30    BD( 43)= 1.00000E-30    BD( 44)= 1.00000E-30    BD( 45)= 1.00000E-30
    BD( 46)= 1.00000E-30    BD( 47)= 1.00000E-30    BD( 48)= 1.00000E-30    BD( 49)= 1.00000E-30    BD( 50)= 1.00000E-30
    BD( 51)= 1.00000E-30    BD( 52)= 1.00000E-30    BD( 53)= 1.00000E-30    BD( 54)= 1.00000E-30    BD( 55)= 4.69500E+05
    BD( 56)= 1.03200E+00    BD( 57)= 1.03200E+00    BD( 58)= 1.00000E-30    BD( 59)= 7.12853E-03    BD( 60)= 1.36774E-02
    BD( 61)= 2.08059E-02    BD( 62)= 1.00000E-30    BD( 63)= 1.00000E-30    BD( 64)= 1.00000E-30    BD( 65)= 1.00000E-30
    BD( 66)= 1.00000E-30    BD( 67)= 1.00000E-30    BD( 68)= 1.00000E-30    BD( 69)= 1.00000E-30    BD( 70)= 1.00000E-30
    BD( 71)= 1.00000E-30    BD( 72)= 1.00000E-30    BD( 73)= 1.00000E-30    BD( 74)= 1.00000E-30    BD( 75)= 5.46109E+00
    BD( 76)= 6.21916E-01    BD( 77)= 1.00000E-30    BD( 78)= 1.00000E-30    BD( 79)= 1.00000E-30    BD( 80)= 1.00000E-30
    BD( 81)= 0.00000E+00    BD( 82)=-2.00000E-01    BD( 83)= 2.00000E-30    BD( 84)= 1.00000E-30    BD( 85)= 1.14629E+00
    BD( 86)= 1.14629E+00    BD( 87)= 1.00000E-30    BD( 88)= 0.00000E+00    BD( 89)= 1.00000E-30    BD( 90)= 2.67928E+07
    BD( 91)= 3.79712E+07    BD( 92)= 2.48495E-03    BD( 93)= 1.83698E+01    BD( 94)= 1.10000E+01    BD( 95)= 1.00000E-30
    BD( 96)= 1.00000E-30    BD( 97)= 1.00000E-30    BD( 98)= 1.00000E-30    BD( 99)= 1.00000E-30    BD(100)= 1.00000E-30
    BD(101)= 1.00000E-30    BD(102)= 1.00000E-30    BD(103)= 1.00000E-30    BD(104)= 1.00000E-30    BD(105)= 1.00000E-30
    BD(106)= 1.00000E-30    BD(107)= 1.00000E-30    BD(108)= 1.00000E-30    BD(109)= 1.00000E-30    BD(110)= 1.00000E-30
    BD(111)= 1.00000E-30    BD(112)= 1.00000E-30    BD(113)= 1.00000E-30    BD(114)= 1.00000E-30    BD(115)= 1.00000E-30
    BD(116)= 1.00000E-30    BD(117)= 1.00000E-30    BD(118)= 1.00000E-30    BD(119)= 1.00000E-30    BD(120)= 1.00000E-30
    BD(121)= 1.00000E-30    BD(122)= 1.00000E-30    BD(123)= 1.00000E-30    BD(124)= 1.00000E-30    BD(125)= 1.00000E-30
    BD(126)= 1.00000E-30    BD(127)= 1.00000E-30    BD(128)= 1.00000E-30    BD(129)= 1.00000E-30    BD(130)= 1.00000E-30
    BD(131)= 1.00000E-30    BD(132)= 1.00000E-30    BD(133)= 1.00000E-30    BD(134)= 1.00000E-30    BD(135)= 1.20000E+00
    BD(136)= 1.20000E+00    BD(137)= 1.20000E+00    BD(138)= 1.20000E+00    BD(139)= 1.20000E+00    BD(140)= 1.20000E+00
    BD(141)= 1.20000E+00    BD(142)= 1.20000E+00    BD(143)= 1.20000E+00    BD(144)= 1.20052E+00    BD(145)= 1.20440E+00
    BD(146)= 1.00000E-30    BD(147)= 1.00000E-30    BD(148)= 1.00000E-30    BD(149)= 1.00000E-30    BD(150)= 1.00000E-30
    BD(151)= 1.00000E-30    BD(152)= 1.00000E-30    BD(153)= 1.00000E-30    BD(154)= 1.00000E-30    BD(155)=-2.05992E-02
    BD(156)=-1.37328E-02    BD(157)=-6.86641E-03    BD(158)= 0.00000E+00    BD(159)= 6.86641E-03    BD(160)= 1.37328E-02
    BD(161)= 2.74656E-02    BD(162)= 4.11985E-02    BD(163)= 5.49313E-02    BD(164)= 6.86641E-02    BD(165)= 8.23969E-02
    BD(166)= 1.00000E-30    BD(167)= 1.00000E-30    BD(168)= 1.00000E-30    BD(169)= 1.00000E-30    BD(170)= 1.00000E-30
    BD(171)= 1.00000E-30    BD(172)= 1.00000E-30    BD(173)= 1.00000E-30    BD(174)= 1.00000E-30    BD(175)= 1.00000E-30
    BD(176)= 1.00000E-30    BD(177)= 1.00000E-30    BD(178)= 1.00000E-30    BD(179)= 1.00000E-30    BD(180)= 1.00000E-30
    BD(181)= 1.00000E-30    BD(182)= 1.00000E-30    BD(183)= 1.00000E-30    BD(184)= 1.00000E-30    BD(185)= 1.00000E-30
    BD(186)= 1.00000E-30    BD(187)= 1.00000E-30    BD(188)= 1.00000E-30    BD(189)= 1.00000E-30    BD(190)= 1.00000E-30
    BD(191)= 1.00000E-30    BD(192)= 1.00000E-30    BD(193)= 1.00000E-30    BD(194)= 1.00000E-30    BD(195)=-0.00000E+00
    BD(196)=-0.00000E+00    BD(197)=-0.00000E+00    BD(198)= 0.00000E+00    BD(199)= 0.00000E+00    BD(200)= 0.00000E+00
    BD(201)= 0.00000E+00    BD(202)= 0.00000E+00    BD(203)= 0.00000E+00    BD(204)= 0.00000E+00    BD(205)= 0.00000E+00
    BD(206)= 1.00000E-30    BD(207)= 1.00000E-30    BD(208)= 1.00000E-30    BD(209)= 1.00000E-30    BD(210)= 1.00000E-30
    BD(211)= 1.00000E-30    BD(212)= 1.00000E-30    BD(213)= 1.00000E-30    BD(214)= 1.00000E-30    BD(215)= 2.15321E-03
    BD(216)= 9.57953E-04    BD(217)= 2.39634E-04    BD(218)= 0.00000E+00    BD(219)= 2.39634E-04    BD(220)= 9.57953E-04
    BD(221)= 3.82248E-03    BD(222)= 8.56564E-03    BD(223)= 1.51411E-02    BD(224)= 2.34845E-02    BD(225)= 3.35139E-02
    BD(226)= 1.00000E-30    BD(227)= 1.00000E-30    BD(228)= 1.00000E-30    BD(229)= 1.00000E-30    BD(230)= 1.00000E-30
    BD(231)= 1.00000E-30    BD(232)= 1.00000E-30    BD(233)= 1.00000E-30    BD(234)= 1.00000E-30    BD(235)= 1.00000E-30
    BD(236)= 1.00000E-30    BD(237)= 1.00000E-30    BD(238)= 1.00000E-30    BD(239)= 1.00000E-30    BD(240)= 1.00000E-30
    BD(241)= 1.00000E-30    BD(242)= 1.00000E-30    BD(243)= 1.00000E-30    BD(244)= 1.00000E-30    BD(245)= 1.00000E-30
    BD(246)= 1.00000E-30    BD(247)= 1.00000E-30    BD(248)= 1.00000E-30    BD(249)= 1.00000E-30    BD(250)= 1.00000E-30
    BD(251)= 1.00000E-30    BD(252)= 1.00000E-30    BD(253)= 1.00000E-30    BD(254)= 1.00000E-30    BD(255)=-6.00000E+00
    BD(256)=-4.00000E+00    BD(257)=-2.00000E+00    BD(258)= 0.00000E+00    BD(259)= 2.00000E+00    BD(260)= 4.00000E+00
    BD(261)= 8.00000E+00    BD(262)= 1.20000E+01    BD(263)= 1.60000E+01    BD(264)= 2.00000E+01    BD(265)= 2.40000E+01
    BD(266)= 1.00000E-30    BD(267)= 1.00000E-30    BD(268)= 1.00000E-30    BD(269)= 1.00000E-30    BD(270)= 1.00000E-30
    BD(271)= 1.00000E-30    BD(272)= 1.00000E-30    BD(273)= 1.00000E-30    BD(274)= 1.00000E-30    BD(275)= 1.00000E-30
    BD(276)= 1.00000E-30    BD(277)= 1.00000E-30    BD(278)= 1.00000E-30    BD(279)= 1.00000E-30    BD(280)= 1.00000E-30
    BD(281)= 1.00000E-30    BD(282)= 1.00000E-30    BD(283)= 1.00000E-30    BD(284)= 1.00000E-30    BD(285)= 1.00000E-30
    BD(286)= 1.00000E-30    BD(287)= 1.00000E-30    BD(288)= 1.00000E-30    BD(289)= 1.00000E-30    BD(290)= 1.00000E-30
    BD(291)= 1.00000E-30    BD(292)= 1.00000E-30    BD(293)= 1.00000E-30    BD(294)= 1.00000E-30    BD(295)= 1.00000E-30
    BD(296)= 1.00000E-30    BD(297)= 1.00000E-30    BD(298)= 1.00000E-30    BD(299)= 1.00000E-30    BD(300)= 1.00000E-30
    BD(301)= 1.00000E-30    BD(302)= 1.00000E-30    BD(303)= 1.00000E-30    BD(304)= 1.00000E-30    BD(305)= 1.00000E-30
    BD(306)= 1.00000E-30    BD(307)= 1.00000E-30    BD(308)= 1.00000E-30    BD(309)= 1.00000E-30    BD(310)= 1.00000E-30
    BD(311)= 1.00000E-30    BD(312)= 1.00000E-30    BD(313)= 1.00000E-30    BD(314)= 1.00000E-30    BD(315)= 1.00000E-30
    BD(316)= 1.00000E-30    BD(317)= 1.00000E-30    BD(318)= 1.00000E-30    BD(319)= 1.00000E-30    BD(320)= 1.00000E-30
    BD(321)= 1.00000E-30    BD(322)= 1.00000E-30    BD(323)= 1.00000E-30    BD(324)= 1.00000E-30    BD(325)= 1.00000E-30
    BD(326)= 1.00000E-30    BD(327)= 1.00000E-30    BD(328)= 1.00000E-30    BD(329)= 1.00000E-30    BD(330)= 1.00000E-30
    BD(331)= 1.00000E-30    BD(332)= 1.00000E-30    BD(333)= 1.00000E-30    BD(334)= 1.00000E-30    BD(335)= 1.00000E-30
    BD(336)= 1.00000E-30    BD(337)= 1.00000E-30    BD(338)= 1.00000E-30    BD(339)= 1.00000E-30    BD(340)= 1.00000E-30
    BD(341)= 1.00000E-30    BD(342)= 1.00000E-30    BD(343)= 1.00000E-30    BD(344)= 1.00000E-30    BD(345)= 1.00000E-30
    BD(346)= 1.00000E-30    BD(347)= 1.00000E-30    BD(348)= 1.00000E-30    BD(349)= 1.00000E-30    BD(350)= 1.00000E-30
    BD(351)= 1.00000E-30    BD(352)= 1.00000E-30    BD(353)= 1.00000E-30    BD(354)= 1.00000E-30    BD(355)= 1.00000E-30
    BD(356)= 1.00000E-30    BD(357)= 1.00000E-30    BD(358)= 1.00000E-30    BD(359)= 1.00000E-30    BD(360)= 1.00000E-30
    BD(361)= 1.00000E-30    BD(362)= 1.00000E-30    BD(363)= 1.00000E-30    BD(364)= 1.00000E-30    BD(365)= 1.00000E-30
    BD(366)= 1.00000E-30    BD(367)= 1.00000E-30    BD(368)= 1.00000E-30    BD(369)= 1.00000E-30    BD(370)= 1.00000E-30
    BD(371)= 1.00000E-30    BD(372)= 1.00000E-30    BD(373)= 1.00000E-30    BD(374)= 1.00000E-30    BD(375)= 1.00000E-30
    BD(376)= 1.00000E-30    BD(377)= 1.00000E-30    BD(378)= 1.00000E-30    BD(379)= 1.00000E-30    BD(380)= 1.00000E-30
    BD(381)= 1.00000E-30    BD(382)= 1.00000E-30    BD(383)= 1.00000E-30    BD(384)= 1.00000E-30    BD(385)= 1.00000E-30
    BD(386)= 1.00000E-30    BD(387)= 1.00000E-30    BD(388)= 1.00000E-30    BD(389)= 1.00000E-30    BD(390)= 1.00000E-30
    BD(391)= 1.00000E-30    BD(392)= 1.00000E-30    BD(393)= 1.00000E-30    BD(394)= 1.00000E-30    BD(395)= 1.00000E-30
    BD(396)= 1.00000E-30    BD(397)= 1.00000E-30    BD(398)= 1.00000E-30    BD(399)= 1.00000E-30    BD(400)= 1.00000E-30
    BD(401)= 1.00000E-30    BD(402)= 1.00000E-30    BD(403)= 1.00000E-30    BD(404)= 1.00000E-30    BD(405)= 1.00000E-30
    BD(406)= 1.00000E-30    BD(407)= 1.00000E-30    BD(408)= 1.00000E-30    BD(409)= 1.00000E-30    BD(410)= 1.00000E-30
    BD(411)= 1.00000E-30    BD(412)= 1.00000E-30    BD(413)= 1.00000E-30    BD(414)= 1.00000E-30    BD(415)= 1.00000E-30
    BD(416)= 1.00000E-30    BD(417)= 1.00000E-30    BD(418)= 1.00000E-30    BD(419)= 1.00000E-30    BD(420)= 1.00000E-30
    BD(421)= 1.00000E-30    BD(422)= 1.00000E-30    BD(423)= 1.00000E-30    BD(424)= 1.00000E-30    BD(425)= 1.00000E-30
    BD(426)= 1.00000E-30    BD(427)= 1.00000E-30    BD(428)= 1.00000E-30    BD(429)= 1.00000E-30    BD(430)= 1.00000E-30
    BD(431)= 1.00000E-30    BD(432)= 1.00000E-30    BD(433)= 1.00000E-30    BD(434)= 1.00000E-30    BD(435)= 1.00000E-30
    BD(436)= 1.00000E-30    BD(437)= 1.00000E-30    BD(438)= 1.00000E-30    BD(439)= 1.00000E-30    BD(440)= 1.00000E-30
    BD(441)= 1.00000E-30    BD(442)= 1.00000E-30    BD(443)= 1.00000E-30    BD(444)= 1.00000E-30    BD(445)= 1.00000E-30
    BD(446)= 1.00000E-30    BD(447)= 1.00000E-30    BD(448)= 1.00000E-30    BD(449)= 1.00000E-30    BD(450)= 1.00000E-30
    BD(451)= 1.00000E-30    BD(452)= 1.00000E-30    BD(453)= 1.00000E-30    BD(454)= 1.00000E-30    BD(455)= 1.00000E-30
    BD(456)= 1.00000E-30    BD(457)= 1.00000E-30    BD(458)= 1.00000E-30    BD(459)= 1.00000E-30    BD(460)= 1.00000E-30
    BD(461)= 1.00000E-30    BD(462)= 1.00000E-30    BD(463)= 1.00000E-30    BD(464)= 1.00000E-30    BD(465)= 1.00000E-30
    BD(466)= 1.00000E-30    BD(467)= 1.00000E-30    BD(468)= 1.00000E-30    BD(469)= 1.00000E-30    BD(470)= 1.00000E-30
    BD(471)= 1.00000E-30    BD(472)= 1.00000E-30    BD(473)= 1.00000E-30    BD(474)= 1.00000E-30    BD(475)= 1.00000E-30
    BD(476)= 1.00000E-30    BD(477)= 1.00000E-30    BD(478)= 1.00000E-30    BD(479)= 1.00000E-30    BD(480)= 1.00000E-30
    BD(481)= 1.00000E-30    BD(482)= 1.00000E-30    BD(483)= 1.00000E-30    BD(484)= 1.00000E-30    BD(485)= 1.00000E-30
    BD(486)= 1.00000E-30    BD(487)= 1.00000E-30    BD(488)= 1.00000E-30    BD(489)= 1.00000E-30    BD(490)= 1.00000E-30
    BD(491)= 1.00000E-30    BD(492)= 1.00000E-30    BD(493)= 1.00000E-30    BD(494)= 1.00000E-30    BD(495)= 1.00000E-30
    BD(496)= 1.00000E-30    BD(497)= 1.00000E-30    BD(498)= 1.00000E-30    BD(499)= 1.00000E-30    BD(500)= 1.00000E-30
    BD(501)= 1.00000E-30    BD(502)= 1.00000E-30    BD(503)= 1.00000E-30    BD(504)= 1.00000E-30    BD(505)= 1.00000E-30
    BD(506)= 1.00000E-30    BD(507)= 1.00000E-30    BD(508)= 1.00000E-30    BD(509)= 1.00000E-30    BD(510)= 1.00000E-30
    BD(511)= 1.00000E-30    BD(512)= 1.00000E-30    BD(513)= 1.00000E-30    BD(514)= 1.00000E-30    BD(515)= 1.00000E-30
    BD(516)= 1.00000E-30    BD(517)= 1.00000E-30    BD(518)= 1.00000E-30    BD(519)= 1.00000E-30    BD(520)= 1.00000E-30
    BD(521)= 1.00000E-30    BD(522)= 1.00000E-30    BD(523)= 1.00000E-30    BD(524)= 1.00000E-30    BD(525)= 1.00000E-30
    BD(526)= 1.00000E-30    BD(527)= 1.00000E-30    BD(528)= 1.00000E-30    BD(529)= 1.00000E-30    BD(530)= 1.00000E-30
    BD(531)= 1.00000E-30    BD(532)= 1.00000E-30    BD(533)= 1.00000E-30    BD(534)= 1.00000E-30    BD(535)= 1.00000E-30
    BD(536)= 1.00000E-30    BD(537)= 1.00000E-30    BD(538)= 1.00000E-30    BD(539)= 1.00000E-30    BD(540)= 1.00000E-30
    BD(541)= 1.00000E-30    BD(542)= 1.00000E-30    BD(543)= 1.00000E-30    BD(544)= 1.00000E-30    BD(545)= 1.00000E-30
    BD(546)= 1.00000E-30    BD(547)= 1.00000E-30    BD(548)= 1.00000E-30    BD(549)= 1.00000E-30    BD(550)= 1.00000E-30
    BD(551)= 1.00000E-30    BD(552)= 1.00000E-30    BD(553)= 1.00000E-30    BD(554)= 1.00000E-30    BD(555)= 1.00000E-30
    BD(556)= 1.00000E-30    BD(557)= 1.00000E-30    BD(558)= 1.00000E-30    BD(559)= 1.00000E-30    BD(560)= 1.00000E-30
    BD(561)= 1.00000E-30    BD(562)= 1.00000E-30    BD(563)= 1.00000E-30    BD(564)= 1.00000E-30    BD(565)= 1.00000E-30
    BD(566)= 1.00000E-30    BD(567)= 1.00000E-30    BD(568)= 1.00000E-30    BD(569)= 1.00000E-30    BD(570)= 1.00000E-30
    BD(571)= 1.00000E-30    BD(572)= 1.00000E-30    BD(573)= 1.00000E-30    BD(574)= 1.00000E-30    BD(575)= 1.00000E-30
    BD(576)= 1.00000E-30    BD(577)= 1.00000E-30    BD(578)= 1.00000E-30    BD(579)= 1.00000E-30    BD(580)= 1.00000E-30
    BD(581)= 1.00000E-30    BD(582)= 1.00000E-30    BD(583)= 1.00000E-30    BD(584)= 1.00000E-30    BD(585)= 1.00000E-30
    BD(586)= 1.00000E-30    BD(587)= 1.00000E-30    BD(588)= 1.00000E-30    BD(589)= 1.00000E-30    BD(590)= 1.00000E-30
    BD(591)= 1.00000E-30    BD(592)= 1.00000E-30    BD(593)= 1.00000E-30    BD(594)= 1.00000E-30    BD(595)= 1.00000E-30
    BD(596)= 1.00000E-30    BD(597)= 1.00000E-30    BD(598)= 1.00000E-30    BD(599)= 1.00000E-30    BD(600)= 1.00000E-30
    BD(601)= 1.00000E-30    BD(602)= 1.00000E-30    BD(603)= 1.00000E-30    BD(604)= 1.00000E-30    BD(605)= 1.00000E-30
    BD(606)= 1.00000E-30    BD(607)= 1.00000E-30    BD(608)= 1.00000E-30    BD(609)= 1.00000E-30    BD(610)= 1.00000E-30
    BD(611)= 1.00000E-30    BD(612)= 1.00000E-30    BD(613)= 1.00000E-30    BD(614)= 1.00000E-30    BD(615)= 1.00000E-30
    BD(616)= 1.00000E-30    BD(617)= 1.00000E-30    BD(618)= 1.00000E-30    BD(619)= 1.00000E-30    BD(620)= 1.00000E-30
    BD(621)= 1.00000E-30    BD(622)= 1.00000E-30    BD(623)= 1.00000E-30    BD(624)= 1.00000E-30    BD(625)= 1.00000E-30
    BD(626)= 1.00000E-30    BD(627)= 1.00000E-30    BD(628)= 1.00000E-30    BD(629)= 1.00000E-30    BD(630)= 1.00000E-30
    BD(631)= 1.00000E-30    BD(632)= 1.00000E-30    BD(633)= 1.00000E-30    BD(634)= 1.00000E-30    BD(635)= 1.00000E-30
    BD(636)= 1.00000E-30    BD(637)= 1.00000E-30    BD(638)= 1.00000E-30    BD(639)= 1.00000E-30    BD(640)= 1.00000E-30
    BD(641)= 1.00000E-30    BD(642)= 1.00000E-30    BD(643)= 1.00000E-30    BD(644)= 1.00000E-30    BD(645)= 1.00000E-30
    BD(646)= 1.00000E-30    BD(647)= 1.00000E-30    BD(648)= 1.00000E-30    BD(649)= 1.00000E-30    BD(650)= 1.00000E-30
    BD(651)= 1.00000E-30    BD(652)= 1.00000E-30    BD(653)= 1.00000E-30    BD(654)= 1.00000E-30    BD(655)= 1.00000E-30
    BD(656)= 1.00000E-30    BD(657)= 1.00000E-30    BD(658)= 1.00000E-30    BD(659)= 1.00000E-30    BD(660)= 1.00000E-30
    BD(661)= 1.00000E-30    BD(662)= 1.00000E-30    BD(663)= 1.00000E-30    BD(664)= 1.00000E-30    BD(665)= 1.00000E-30
    BD(666)= 1.00000E-30    BD(667)= 1.00000E-30    BD(668)= 1.00000E-30    BD(669)= 1.00000E-30    BD(670)= 1.00000E-30
    BD(671)= 1.00000E-30    BD(672)= 1.00000E-30    BD(673)= 1.00000E-30    BD(674)= 1.00000E-30    BD(675)= 1.00000E-30
    BD(676)= 1.00000E-30    BD(677)= 1.00000E-30    BD(678)= 1.00000E-30    BD(679)= 1.00000E-30    BD(680)= 1.00000E-30
    BD(681)= 1.00000E-30    BD(682)= 1.00000E-30    BD(683)= 1.00000E-30    BD(684)= 1.00000E-30    BD(685)= 1.00000E-30
    BD(686)= 1.00000E-30    BD(687)= 1.00000E-30    BD(688)= 1.00000E-30    BD(689)= 1.00000E-30    BD(690)= 1.00000E-30
    BD(691)= 1.00000E-30    BD(692)= 1.00000E-30    BD(693)= 1.00000E-30    BD(694)= 1.00000E-30    BD(695)= 1.00000E-30
    BD(696)= 1.00000E-30    BD(697)= 1.00000E-30    BD(698)= 1.00000E-30    BD(699)= 1.00000E-30    BD(700)= 1.00000E-30
    BD(701)= 1.00000E-30    BD(702)= 1.00000E-30    BD(703)= 1.00000E-30    BD(704)= 1.00000E-30    BD(705)= 1.00000E-30
    BD(706)= 1.00000E-30    BD(707)= 1.00000E-30    BD(708)= 1.00000E-30    BD(709)= 1.00000E-30    BD(710)= 1.00000E-30
    BD(711)= 1.00000E-30    BD(712)= 1.00000E-30    BD(713)= 1.00000E-30    BD(714)= 1.00000E-30    BD(715)= 1.00000E-30
    BD(716)= 1.00000E-30    BD(717)= 1.00000E-30    BD(718)= 1.00000E-30    BD(719)= 1.00000E-30    BD(720)= 1.00000E-30
    BD(721)= 1.00000E-30    BD(722)= 1.00000E-30    BD(723)= 1.00000E-30    BD(724)= 1.00000E-30    BD(725)= 1.00000E-30
    BD(726)= 1.00000E-30    BD(727)= 1.00000E-30    BD(728)= 1.00000E-30    BD(729)= 1.00000E-30    BD(730)= 1.00000E-30
    BD(731)= 1.00000E-30    BD(732)= 1.00000E-30    BD(733)= 1.00000E-30    BD(734)= 1.00000E-30    BD(735)= 1.00000E-30
    BD(736)= 1.00000E-30    BD(737)= 1.00000E-30    BD(738)= 1.00000E-30    BD(739)= 1.00000E-30    BD(740)= 1.00000E-30
    BD(741)= 1.00000E-30    BD(742)= 1.00000E-30    BD(743)= 1.00000E-30    BD(744)= 1.00000E-30    BD(745)= 1.00000E-30
    BD(746)= 1.00000E-30    BD(747)= 1.00000E-30    BD(748)= 1.00000E-30    BD(749)= 1.00000E-30    BD(750)= 1.00000E-30
    BD(751)= 1.00000E-30    BD(752)= 1.00000E-30    BD(753)= 1.00000E-30    BD(754)= 1.00000E-30    BD(755)= 1.00000E-30
    BD(756)= 1.00000E-30    BD(757)= 1.00000E-30    BD(758)= 1.00000E-30    BD(759)= 1.00000E-30    BD(760)= 1.00000E-30
    BD(761)= 1.00000E-30    BD(762)= 1.00000E-30
 
   STB(  1)= 1.00000E-30   STB(  2)= 0.00000E+00   STB(  3)= 1.00000E+00   STB(  4)= 1.00000E-30   STB(  5)= 1.00000E-30
   STB(  6)= 1.00000E-30   STB(  7)= 1.00000E-30   STB(  8)= 1.00000E-30   STB(  9)= 1.00000E-30   STB( 10)= 1.00000E-30
   STB( 11)= 1.00000E-30   STB( 12)= 1.00000E-30   STB( 13)= 1.00000E-30   STB( 14)= 1.00000E-30   STB( 15)= 1.00000E-30
   STB( 16)= 1.00000E-30   STB( 17)= 1.00000E-30   STB( 18)= 1.00000E-30   STB( 19)= 1.00000E-30   STB( 20)= 1.00000E-30
   STB( 21)= 1.00000E-30   STB( 22)= 1.00000E-30   STB( 23)= 1.00000E-30   STB( 24)= 1.00000E-30   STB( 25)= 1.00000E-30
   STB( 26)= 1.00000E-30   STB( 27)= 1.00000E-30   STB( 28)= 1.00000E-30   STB( 29)= 1.00000E-30   STB( 30)= 1.00000E-30
   STB( 31)= 1.00000E-30   STB( 32)= 1.00000E-30   STB( 33)= 1.00000E-30   STB( 34)= 1.00000E-30   STB( 35)= 1.00000E-30
   STB( 36)= 1.00000E-30   STB( 37)= 1.00000E-30   STB( 38)= 1.00000E-30   STB( 39)= 1.00000E-30   STB( 40)= 1.00000E-30
   STB( 41)= 1.00000E-30   STB( 42)= 1.00000E-30   STB( 43)= 1.00000E-30   STB( 44)= 1.00000E-30   STB( 45)= 1.00000E-30
   STB( 46)= 1.00000E-30   STB( 47)= 1.00000E-30   STB( 48)= 1.00000E-30   STB( 49)= 1.00000E-30   STB( 50)= 1.00000E-30
   STB( 51)= 1.00000E-30   STB( 52)= 1.00000E-30   STB( 53)= 1.00000E-30   STB( 54)= 1.00000E-30   STB( 55)= 1.00000E-30
   STB( 56)= 1.00000E-30   STB( 57)= 1.00000E-30   STB( 58)= 1.00000E-30   STB( 59)= 1.00000E-30   STB( 60)= 1.00000E-30
   STB( 61)= 1.00000E-30   STB( 62)= 1.00000E-30   STB( 63)= 1.00000E-30   STB( 64)= 1.00000E-30   STB( 65)= 1.00000E-30
   STB( 66)= 1.00000E-30   STB( 67)= 1.00000E-30   STB( 68)= 1.00000E-30   STB( 69)= 1.00000E-30   STB( 70)= 1.00000E-30
   STB( 71)= 1.00000E-30   STB( 72)= 1.00000E-30   STB( 73)= 1.00000E-30   STB( 74)= 1.00000E-30   STB( 75)= 1.00000E-30
   STB( 76)= 1.00000E-30   STB( 77)= 1.00000E-30   STB( 78)= 1.00000E-30   STB( 79)= 1.00000E-30   STB( 80)= 1.00000E-30
   STB( 81)= 1.00000E-30   STB( 82)= 1.00000E-30   STB( 83)= 1.00000E-30   STB( 84)= 1.00000E-30   STB( 85)= 1.00000E-30
   STB( 86)= 1.00000E-30   STB( 87)= 1.00000E-30   STB( 88)= 1.00000E-30   STB( 89)= 1.00000E-30   STB( 90)= 1.00000E-30
   STB( 91)= 1.00000E-30   STB( 92)= 1.00000E-30   STB( 93)= 1.00000E-30   STB( 94)= 1.00000E-30   STB( 95)= 1.00000E-30
   STB( 96)= 1.00000E-30   STB( 97)= 1.00000E-30   STB( 98)= 1.00000E-30   STB( 99)= 1.00000E-30   STB(100)= 1.00000E-30
   STB(101)= 1.00000E-30   STB(102)= 1.00000E-30   STB(103)= 1.00000E-30   STB(104)= 1.00000E-30   STB(105)= 1.00000E-30
   STB(106)= 1.00000E-30   STB(107)= 1.00000E-30   STB(108)= 1.00000E-30   STB(109)= 1.00000E-30   STB(110)= 1.00000E-30
   STB(111)= 1.00000E-30   STB(112)= 1.00000E-30   STB(113)= 1.00000E-30   STB(114)= 1.00000E-30   STB(115)= 1.00000E-30
   STB(116)= 1.00000E-30   STB(117)= 1.00000E-30   STB(118)= 1.00000E-30   STB(119)= 1.00000E-30   STB(120)= 1.00000E-30
   STB(121)= 1.00000E-30   STB(122)= 1.00000E-30   STB(123)= 1.00000E-30   STB(124)= 1.00000E-30   STB(125)= 1.00000E-30
   STB(126)= 1.00000E-30   STB(127)= 1.00000E-30   STB(128)= 1.00000E-30   STB(129)= 1.00000E-30   STB(130)= 1.00000E-30
   STB(131)= 1.00000E-30   STB(132)= 1.00000E-30   STB(133)= 1.00000E-30   STB(134)= 1.00000E-30   STB(135)= 1.00000E-30
0**** FOLLOWING ARE THE BASIC INPUT DATA BLOCKS ****
 
   FLC(  1)= 1.00000E+00   FLC(  2)= 1.10000E+01   FLC(  3)= 6.00000E-01   FLC(  4)= 1.00000E-30   FLC(  5)= 1.00000E-30
   FLC(  6)= 1.00000E-30   FLC(  7)= 1.00000E-30   FLC(  8)= 1.00000E-30   FLC(  9)= 1.00000E-30   FLC( 10)= 1.00000E-30
   FLC( 11)= 1.00000E-30   FLC( 12)= 1.00000E-30   FLC( 13)= 1.00000E-30   FLC( 14)= 1.00000E-30   FLC( 15)= 1.00000E-30
   FLC( 16)= 1.00000E-30   FLC( 17)= 1.00000E-30   FLC( 18)= 1.00000E-30   FLC( 19)= 1.00000E-30   FLC( 20)= 1.00000E-30
   FLC( 21)= 1.00000E-30   FLC( 22)= 1.00000E-30   FLC( 23)=-6.00000E+00   FLC( 24)=-4.00000E+00   FLC( 25)=-2.00000E+00
   FLC( 26)= 0.00000E+00   FLC( 27)= 2.00000E+00   FLC( 28)= 4.00000E+00   FLC( 29)= 8.00000E+00   FLC( 30)= 1.20000E+01
   FLC( 31)= 1.60000E+01   FLC( 32)= 2.00000E+01   FLC( 33)= 2.40000E+01   FLC( 34)= 1.00000E-30   FLC( 35)= 1.00000E-30
   FLC( 36)= 1.00000E-30   FLC( 37)= 1.00000E-30   FLC( 38)= 1.00000E-30   FLC( 39)= 1.00000E-30   FLC( 40)= 1.00000E-30
   FLC( 41)= 1.00000E-30   FLC( 42)= 1.00000E-30   FLC( 43)= 4.28000E+06   FLC( 44)= 1.00000E-30   FLC( 45)= 1.00000E-30
   FLC( 46)= 1.00000E-30   FLC( 47)= 1.00000E-30   FLC( 48)= 1.00000E-30   FLC( 49)= 1.00000E-30   FLC( 50)= 1.00000E-30
   FLC( 51)= 1.00000E-30   FLC( 52)= 1.00000E-30   FLC( 53)= 1.00000E-30   FLC( 54)= 1.00000E-30   FLC( 55)= 1.00000E-30
   FLC( 56)= 1.00000E-30   FLC( 57)= 1.00000E-30   FLC( 58)= 1.00000E-30   FLC( 59)= 1.00000E-30   FLC( 60)= 1.00000E-30
   FLC( 61)= 1.00000E-30   FLC( 62)= 1.00000E-30   FLC( 63)= 1.00000E-30   FLC( 64)= 1.00000E-30   FLC( 65)= 1.00000E-30
   FLC( 66)= 1.00000E-30   FLC( 67)= 1.00000E-30   FLC( 68)= 1.00000E-30   FLC( 69)= 1.00000E-30   FLC( 70)= 1.00000E-30
   FLC( 71)= 1.00000E-30   FLC( 72)= 1.00000E-30   FLC( 73)= 1.00000E-30   FLC( 74)=-1.00000E-30   FLC( 75)= 1.00000E-30
   FLC( 76)= 1.00000E-30   FLC( 77)= 1.00000E-30   FLC( 78)= 1.00000E-30   FLC( 79)= 1.00000E-30   FLC( 80)= 1.00000E-30
   FLC( 81)= 1.00000E-30   FLC( 82)= 1.00000E-30   FLC( 83)= 1.00000E-30   FLC( 84)= 1.00000E-30   FLC( 85)= 1.00000E-30
   FLC( 86)= 1.00000E-30   FLC( 87)= 1.00000E-30   FLC( 88)= 1.00000E-30   FLC( 89)= 1.00000E-30   FLC( 90)= 1.00000E-30
   FLC( 91)= 1.00000E-30   FLC( 92)= 1.00000E-30   FLC( 93)= 1.00000E-30   FLC( 94)= 6.00000E-01   FLC( 95)= 1.40000E+00
   FLC( 96)= 0.00000E+00   FLC( 97)=-1.00000E-30   FLC( 98)= 1.00000E-30   FLC( 99)= 1.00000E-30   FLC(100)= 1.00000E-30
   FLC(101)= 1.00000E-30   FLC(102)= 1.00000E-30   FLC(103)= 1.00000E-30   FLC(104)= 1.00000E-30   FLC(105)= 1.00000E-30
   FLC(106)= 1.00000E-30   FLC(107)= 1.00000E-30   FLC(108)= 1.00000E-30   FLC(109)= 1.00000E-30   FLC(110)= 1.00000E-30
   FLC(111)= 1.00000E-30   FLC(112)= 1.00000E-30   FLC(113)= 1.00000E-30   FLC(114)= 1.00000E-30   FLC(115)= 1.00000E-30
   FLC(116)= 1.00000E-30   FLC(117)=-1.00000E-30   FLC(118)= 1.00000E-30   FLC(119)= 1.00000E-30   FLC(120)= 1.00000E-30
   FLC(121)= 1.00000E-30   FLC(122)= 1.00000E-30   FLC(123)= 1.00000E-30   FLC(124)= 1.00000E-30   FLC(125)= 1.00000E-30
   FLC(126)= 1.00000E-30   FLC(127)= 1.00000E-30   FLC(128)= 1.00000E-30   FLC(129)= 1.00000E-30   FLC(130)= 1.00000E-30
   FLC(131)= 1.00000E-30   FLC(132)= 1.00000E-30   FLC(133)= 1.00000E-30   FLC(134)= 1.00000E-30   FLC(135)= 1.00000E-30
   FLC(136)= 1.00000E-30   FLC(137)=-1.00000E-30   FLC(138)= 1.00000E-30   FLC(139)= 1.00000E-30   FLC(140)= 1.00000E-30
   FLC(141)= 1.00000E-30   FLC(142)= 1.00000E-30   FLC(143)= 1.00000E-30   FLC(144)= 1.00000E-30   FLC(145)= 1.00000E-30
   FLC(146)= 1.00000E-30   FLC(147)= 1.00000E-30   FLC(148)= 1.00000E-30   FLC(149)= 1.00000E-30   FLC(150)= 1.00000E-30
   FLC(151)= 1.00000E-30   FLC(152)= 1.00000E-30   FLC(153)= 1.00000E-30   FLC(154)= 1.00000E-30   FLC(155)= 1.00000E-30
   FLC(156)= 1.00000E-30   FLC(157)= 1.00000E-30   FLC(158)= 1.00000E-30   FLC(159)= 0.00000E+00   FLC(160)= 1.00000E+00
 
  OPTI(  1)= 8.85000E+00  OPTI(  2)= 2.48000E+00  OPTI(  3)= 1.60000E-04  OPTI(  4)= 4.28000E+00
 
  SYNA(  1)= 4.14000E+00  SYNA(  2)= 1.00000E-30  SYNA(  3)= 1.00000E-30  SYNA(  4)= 1.00000E-30  SYNA(  5)=-2.00000E-01
  SYNA(  6)= 1.00000E-30  SYNA(  7)= 1.00000E-30  SYNA(  8)= 1.00000E-30  SYNA(  9)= 1.00000E-30  SYNA( 10)= 1.40130E-45
  SYNA( 11)= 1.00000E-30  SYNA( 12)= 1.00000E-30  SYNA( 13)= 1.00000E+00  SYNA( 14)= 1.00000E-30  SYNA( 15)= 1.00000E-30
  SYNA( 16)= 1.00000E-30  SYNA( 17)= 1.00000E-30  SYNA( 18)= 1.00000E-30  SYNA( 19)= 1.00000E-30
 
  BDIN(  1)= 1.00000E+01  BDIN(  2)= 0.00000E+00  BDIN(  3)= 2.58000E-01  BDIN(  4)= 5.89000E-01  BDIN(  5)= 1.26000E+00
  BDIN(  6)= 2.26000E+00  BDIN(  7)= 2.59000E+00  BDIN(  8)= 2.93000E+00  BDIN(  9)= 3.59000E+00  BDIN( 10)= 4.57000E+00
  BDIN( 11)= 6.26000E+00  BDIN( 12)= 1.00000E-30  BDIN( 13)= 1.00000E-30  BDIN( 14)= 1.00000E-30  BDIN( 15)= 1.00000E-30
  BDIN( 16)= 1.00000E-30  BDIN( 17)= 1.00000E-30  BDIN( 18)= 1.00000E-30  BDIN( 19)= 1.00000E-30  BDIN( 20)= 1.00000E-30
  BDIN( 21)= 1.00000E-30  BDIN( 22)= 0.00000E+00  BDIN( 23)= 8.00000E-02  BDIN( 24)= 1.60000E-01  BDIN( 25)= 3.23000E-01
  BDIN( 26)= 7.51000E-01  BDIN( 27)= 8.83000E-01  BDIN( 28)= 9.39000E-01  BDIN( 29)= 1.03200E+00  BDIN( 30)= 1.03200E+00
  BDIN( 31)= 1.03200E+00  BDIN( 32)= 1.00000E-30  BDIN( 33)= 1.00000E-30  BDIN( 34)= 1.00000E-30  BDIN( 35)= 1.00000E-30
  BDIN( 36)= 1.00000E-30  BDIN( 37)= 1.00000E-30  BDIN( 38)= 1.00000E-30  BDIN( 39)= 1.00000E-30  BDIN( 40)= 1.00000E-30
  BDIN( 41)= 1.00000E-30  BDIN( 42)= 0.00000E+00  BDIN( 43)= 1.00000E+00  BDIN( 44)= 1.42000E+00  BDIN( 45)= 2.01000E+00
  BDIN( 46)= 3.08000E+00  BDIN( 47)= 3.34000E+00  BDIN( 48)= 3.44000E+00  BDIN( 49)= 3.61000E+00  BDIN( 50)= 3.61000E+00
  BDIN( 51)= 3.61000E+00  BDIN( 52)= 1.00000E-30  BDIN( 53)= 1.00000E-30  BDIN( 54)= 1.00000E-30  BDIN( 55)= 1.00000E-30
  BDIN( 56)= 1.00000E-30  BDIN( 57)= 1.00000E-30  BDIN( 58)= 1.00000E-30  BDIN( 59)= 1.00000E-30  BDIN( 60)= 1.00000E-30
  BDIN( 61)= 1.00000E-30  BDIN( 62)= 0.00000E+00  BDIN( 63)= 1.86000E-01  BDIN( 64)= 2.86000E-01  BDIN( 65)= 4.24000E-01
  BDIN( 66)= 5.33000E-01  BDIN( 67)= 5.33000E-01  BDIN( 68)= 5.33000E-01  BDIN( 69)= 5.33000E-01  BDIN( 70)= 5.33000E-01
  BDIN( 71)= 5.33000E-01  BDIN( 72)= 1.00000E-30  BDIN( 73)= 1.00000E-30  BDIN( 74)= 1.00000E-30  BDIN( 75)= 1.00000E-30
  BDIN( 76)= 1.00000E-30  BDIN( 77)= 1.00000E-30  BDIN( 78)= 1.00000E-30  BDIN( 79)= 1.00000E-30  BDIN( 80)= 1.00000E-30
  BDIN( 81)= 1.00000E-30  BDIN( 82)= 1.00000E-30  BDIN( 83)= 1.00000E-30  BDIN( 84)= 1.00000E-30  BDIN( 85)= 1.00000E-30
  BDIN( 86)= 1.00000E-30  BDIN( 87)= 1.00000E-30  BDIN( 88)= 1.00000E-30  BDIN( 89)= 1.00000E-30  BDIN( 90)= 1.00000E-30
  BDIN( 91)= 1.00000E-30  BDIN( 92)= 1.00000E-30  BDIN( 93)= 1.00000E-30  BDIN( 94)= 1.00000E-30  BDIN( 95)= 1.00000E-30
  BDIN( 96)= 1.00000E-30  BDIN( 97)= 1.00000E-30  BDIN( 98)= 1.00000E-30  BDIN( 99)= 1.00000E-30  BDIN(100)= 1.00000E-30
  BDIN(101)= 1.00000E-30  BDIN(102)= 1.00000E-30  BDIN(103)= 1.00000E-30  BDIN(104)= 1.00000E-30  BDIN(105)= 1.00000E-30
  BDIN(106)= 1.00000E-30  BDIN(107)= 1.00000E-30  BDIN(108)= 1.00000E-30  BDIN(109)= 1.00000E-30  BDIN(110)= 1.00000E-30
  BDIN(111)= 1.00000E-30  BDIN(112)= 1.00000E-30  BDIN(113)= 1.00000E-30  BDIN(114)= 1.00000E-30  BDIN(115)= 1.00000E-30
  BDIN(116)= 1.00000E-30  BDIN(117)= 1.00000E-30  BDIN(118)= 1.00000E-30  BDIN(119)= 1.00000E-30  BDIN(120)= 1.00000E-30
  BDIN(121)= 1.00000E-30  BDIN(122)= 1.00000E+00  BDIN(123)= 1.00000E-30  BDIN(124)= 2.59000E+00  BDIN(125)= 3.67000E+00
  BDIN(126)= 1.00000E-30  BDIN(127)= 2.00000E+00  BDIN(128)= 1.00000E+00  BDIN(129)= 1.00000E+00
0**** FOLLOWING ARE THE IOM DATA BLOCKS ****
 
  BODY(  1)= 2.29591E-02  BODY(  2)= 2.17639E-02  BODY(  3)= 2.10455E-02  BODY(  4)= 2.08059E-02  BODY(  5)= 2.10455E-02
  BODY(  6)= 2.17639E-02  BODY(  7)= 2.46284E-02  BODY(  8)= 2.93715E-02  BODY(  9)= 3.59470E-02  BODY( 10)= 4.42904E-02
  BODY( 11)= 5.43198E-02  BODY( 12)= 1.00000E-30  BODY( 13)= 1.00000E-30  BODY( 14)= 1.00000E-30  BODY( 15)= 1.00000E-30
  BODY( 16)= 1.00000E-30  BODY( 17)= 1.00000E-30  BODY( 18)= 1.00000E-30  BODY( 19)= 1.00000E-30  BODY( 20)= 1.00000E-30
  BODY( 21)=-2.05992E-02  BODY( 22)=-1.37328E-02  BODY( 23)=-6.86641E-03  BODY( 24)= 0.00000E+00  BODY( 25)= 6.86641E-03
  BODY( 26)= 1.37328E-02  BODY( 27)= 2.74656E-02  BODY( 28)= 4.11985E-02  BODY( 29)= 5.49313E-02  BODY( 30)= 6.86641E-02
  BODY( 31)= 8.23969E-02  BODY( 32)= 1.00000E-30  BODY( 33)= 1.00000E-30  BODY( 34)= 1.00000E-30  BODY( 35)= 1.00000E-30
  BODY( 36)= 1.00000E-30  BODY( 37)= 1.00000E-30  BODY( 38)= 1.00000E-30  BODY( 39)= 1.00000E-30  BODY( 40)= 1.00000E-30
  BODY( 41)=-2.04910E-02  BODY( 42)=-1.36607E-02  BODY( 43)=-6.83034E-03  BODY( 44)= 0.00000E+00  BODY( 45)= 6.83034E-03
  BODY( 46)= 1.36607E-02  BODY( 47)= 2.73214E-02  BODY( 48)= 4.09820E-02  BODY( 49)= 5.46427E-02  BODY( 50)= 6.83034E-02
  BODY( 51)= 8.19641E-02  BODY( 52)= 1.00000E-30  BODY( 53)= 1.00000E-30  BODY( 54)= 1.00000E-30  BODY( 55)= 1.00000E-30
  BODY( 56)= 1.00000E-30  BODY( 57)= 1.00000E-30  BODY( 58)= 1.00000E-30  BODY( 59)= 1.00000E-30  BODY( 60)= 1.00000E-30
  BODY( 61)=-2.28863E-02  BODY( 62)=-1.52175E-02  BODY( 63)=-7.59671E-03  BODY( 64)= 0.00000E+00  BODY( 65)= 7.59671E-03
  BODY( 66)= 1.52175E-02  BODY( 67)= 3.06260E-02  BODY( 68)= 4.64049E-02  BODY( 69)= 6.27117E-02  BODY( 70)= 7.96714E-02
  BODY( 71)= 9.73672E-02  BODY( 72)= 1.00000E-30  BODY( 73)= 1.00000E-30  BODY( 74)= 1.00000E-30  BODY( 75)= 1.00000E-30
  BODY( 76)= 1.00000E-30  BODY( 77)= 1.00000E-30  BODY( 78)= 1.00000E-30  BODY( 79)= 1.00000E-30  BODY( 80)= 1.00000E-30
  BODY( 81)= 2.06801E-02  BODY( 82)= 2.07529E-02  BODY( 83)= 2.07931E-02  BODY( 84)= 2.08059E-02  BODY( 85)= 2.07931E-02
  BODY( 86)= 2.07529E-02  BODY( 87)= 2.05662E-02  BODY( 88)= 2.01641E-02  BODY( 89)= 1.94134E-02  BODY( 90)= 1.81349E-02
  BODY( 91)= 1.61097E-02  BODY( 92)= 1.00000E-30  BODY( 93)= 1.00000E-30  BODY( 94)= 1.00000E-30  BODY( 95)= 1.00000E-30
  BODY( 96)= 1.00000E-30  BODY( 97)= 1.00000E-30  BODY( 98)= 1.00000E-30  BODY( 99)= 1.00000E-30  BODY(100)= 1.00000E-30
  BODY(101)= 3.43321E-03  BODY(102)= 3.43321E-03  BODY(103)= 3.43321E-03  BODY(104)= 3.43321E-03  BODY(105)= 3.43321E-03
  BODY(106)= 3.43320E-03  BODY(107)= 3.43321E-03  BODY(108)= 3.43321E-03  BODY(109)= 3.43321E-03  BODY(110)= 3.43321E-03
  BODY(111)= 3.43321E-03  BODY(112)= 1.00000E-30  BODY(113)= 1.00000E-30  BODY(114)= 1.00000E-30  BODY(115)= 1.00000E-30
  BODY(116)= 1.00000E-30  BODY(117)= 1.00000E-30  BODY(118)= 1.00000E-30  BODY(119)= 1.00000E-30  BODY(120)= 1.00000E-30
  BODY(121)= 3.41517E-03  BODY(122)= 3.41517E-03  BODY(123)= 3.41517E-03  BODY(124)= 3.41517E-03  BODY(125)= 3.41517E-03
  BODY(126)= 3.41517E-03  BODY(127)= 3.41517E-03  BODY(128)= 3.41517E-03  BODY(129)= 3.41517E-03  BODY(130)= 3.41517E-03
  BODY(131)= 3.41517E-03  BODY(132)= 1.00000E-30  BODY(133)= 1.00000E-30  BODY(134)= 1.00000E-30  BODY(135)= 1.00000E-30
  BODY(136)= 1.00000E-30  BODY(137)= 1.00000E-30  BODY(138)= 1.00000E-30  BODY(139)= 1.00000E-30  BODY(140)= 1.00000E-30
  BODY(141)=-3.43321E-03  BODY(142)=-3.43321E-03  BODY(143)=-3.43321E-03  BODY(144)=-3.43321E-03  BODY(145)=-3.43321E-03
  BODY(146)=-3.43320E-03  BODY(147)=-3.43321E-03  BODY(148)=-3.43321E-03  BODY(149)=-3.43321E-03  BODY(150)=-3.43321E-03
  BODY(151)=-3.43321E-03  BODY(152)= 1.00000E-30  BODY(153)= 1.00000E-30  BODY(154)= 1.00000E-30  BODY(155)= 1.00000E-30
  BODY(156)= 1.00000E-30  BODY(157)= 1.00000E-30  BODY(158)= 1.00000E-30  BODY(159)= 1.00000E-30  BODY(160)= 1.00000E-30
  BODY(161)=-1.97888E-03  BODY(162)=-1.97888E-03  BODY(163)=-1.97888E-03  BODY(164)=-1.97888E-03  BODY(165)=-1.97888E-03
  BODY(166)=-1.97888E-03  BODY(167)=-1.97888E-03  BODY(168)=-1.97888E-03  BODY(169)=-1.97888E-03  BODY(170)=-1.97889E-03
  BODY(171)=-1.97889E-03  BODY(172)= 1.00000E-30  BODY(173)= 1.00000E-30  BODY(174)= 1.00000E-30  BODY(175)= 1.00000E-30
  BODY(176)= 1.00000E-30  BODY(177)= 1.00000E-30  BODY(178)= 1.00000E-30  BODY(179)= 1.00000E-30  BODY(180)= 1.00000E-30
  BODY(181)= 0.00000E+00  BODY(182)= 0.00000E+00  BODY(183)= 0.00000E+00  BODY(184)= 0.00000E+00  BODY(185)= 0.00000E+00
  BODY(186)= 0.00000E+00  BODY(187)= 0.00000E+00  BODY(188)= 0.00000E+00  BODY(189)= 0.00000E+00  BODY(190)= 0.00000E+00
  BODY(191)= 0.00000E+00  BODY(192)= 1.00000E-30  BODY(193)= 1.00000E-30  BODY(194)= 1.00000E-30  BODY(195)= 1.00000E-30
  BODY(196)= 1.00000E-30  BODY(197)= 1.00000E-30  BODY(198)= 1.00000E-30  BODY(199)= 1.00000E-30  BODY(200)= 1.00000E-30
  BODY(201)= 1.00000E-30  BODY(202)= 1.00000E-30  BODY(203)= 1.00000E-30  BODY(204)= 1.00000E-30  BODY(205)= 1.00000E-30
  BODY(206)= 1.00000E-30  BODY(207)= 1.00000E-30  BODY(208)= 1.00000E-30  BODY(209)= 1.00000E-30  BODY(210)= 1.00000E-30
  BODY(211)= 1.00000E-30  BODY(212)= 1.00000E-30  BODY(213)= 1.00000E-30  BODY(214)= 1.00000E-30  BODY(215)= 1.00000E-30
  BODY(216)= 1.00000E-30  BODY(217)= 1.00000E-30  BODY(218)= 1.00000E-30  BODY(219)= 1.00000E-30  BODY(220)= 1.00000E-30
  BODY(221)= 1.00000E-30  BODY(222)= 1.00000E-30  BODY(223)= 1.00000E-30  BODY(224)= 1.00000E-30  BODY(225)= 1.00000E-30
  BODY(226)= 1.00000E-30  BODY(227)= 1.00000E-30  BODY(228)= 1.00000E-30  BODY(229)= 1.00000E-30  BODY(230)= 1.00000E-30
  BODY(231)= 1.00000E-30  BODY(232)= 1.00000E-30  BODY(233)= 1.00000E-30  BODY(234)= 1.00000E-30  BODY(235)= 1.00000E-30
  BODY(236)= 1.00000E-30  BODY(237)= 1.00000E-30  BODY(238)= 1.00000E-30  BODY(239)= 1.00000E-30  BODY(240)= 1.00000E-30
  BODY(241)= 1.00000E-30  BODY(242)= 1.00000E-30  BODY(243)= 1.00000E-30  BODY(244)= 1.00000E-30  BODY(245)= 1.00000E-30
  BODY(246)= 1.00000E-30  BODY(247)= 1.00000E-30  BODY(248)= 1.00000E-30  BODY(249)= 1.00000E-30  BODY(250)= 1.00000E-30
  BODY(251)= 1.00000E-30  BODY(252)= 1.00000E-30  BODY(253)= 1.00000E-30  BODY(254)= 1.00000E-30  BODY(255)= 1.00000E-30
  BODY(256)= 1.00000E-30  BODY(257)= 1.00000E-30  BODY(258)= 1.00000E-30  BODY(259)= 1.00000E-30  BODY(260)= 1.00000E-30
  BODY(261)= 1.00000E-30  BODY(262)= 1.00000E-30  BODY(263)= 1.00000E-30  BODY(264)= 1.00000E-30  BODY(265)= 1.00000E-30
  BODY(266)= 1.00000E-30  BODY(267)= 1.00000E-30  BODY(268)= 1.00000E-30  BODY(269)= 1.00000E-30  BODY(270)= 1.00000E-30
  BODY(271)= 1.00000E-30  BODY(272)= 1.00000E-30  BODY(273)= 1.00000E-30  BODY(274)= 1.00000E-30  BODY(275)= 1.00000E-30
  BODY(276)= 1.00000E-30  BODY(277)= 1.00000E-30  BODY(278)= 1.00000E-30  BODY(279)= 1.00000E-30  BODY(280)= 1.00000E-30
  BODY(281)= 1.00000E-30  BODY(282)= 1.00000E-30  BODY(283)= 1.00000E-30  BODY(284)= 1.00000E-30  BODY(285)= 1.00000E-30
  BODY(286)= 1.00000E-30  BODY(287)= 1.00000E-30  BODY(288)= 1.00000E-30  BODY(289)= 1.00000E-30  BODY(290)= 1.00000E-30
  BODY(291)= 1.00000E-30  BODY(292)= 1.00000E-30  BODY(293)= 1.00000E-30  BODY(294)= 1.00000E-30  BODY(295)= 1.00000E-30
  BODY(296)= 1.00000E-30  BODY(297)= 1.00000E-30  BODY(298)= 1.00000E-30  BODY(299)= 1.00000E-30  BODY(300)= 1.00000E-30
  BODY(301)= 1.00000E-30  BODY(302)= 1.00000E-30  BODY(303)= 1.00000E-30  BODY(304)= 1.00000E-30  BODY(305)= 1.00000E-30
  BODY(306)= 1.00000E-30  BODY(307)= 1.00000E-30  BODY(308)= 1.00000E-30  BODY(309)= 1.00000E-30  BODY(310)= 1.00000E-30
  BODY(311)= 1.00000E-30  BODY(312)= 1.00000E-30  BODY(313)= 1.00000E-30  BODY(314)= 1.00000E-30  BODY(315)= 1.00000E-30
  BODY(316)= 1.00000E-30  BODY(317)= 1.00000E-30  BODY(318)= 1.00000E-30  BODY(319)= 1.00000E-30  BODY(320)= 1.00000E-30
  BODY(321)= 1.00000E-30  BODY(322)= 1.00000E-30  BODY(323)= 1.00000E-30  BODY(324)= 1.00000E-30  BODY(325)= 1.00000E-30
  BODY(326)= 1.00000E-30  BODY(327)= 1.00000E-30  BODY(328)= 1.00000E-30  BODY(329)= 1.00000E-30  BODY(330)= 1.00000E-30
  BODY(331)= 1.00000E-30  BODY(332)= 1.00000E-30  BODY(333)= 1.00000E-30  BODY(334)= 1.00000E-30  BODY(335)= 1.00000E-30
  BODY(336)= 1.00000E-30  BODY(337)= 1.00000E-30  BODY(338)= 1.00000E-30  BODY(339)= 1.00000E-30  BODY(340)= 1.00000E-30
  BODY(341)= 1.00000E-30  BODY(342)= 1.00000E-30  BODY(343)= 1.00000E-30  BODY(344)= 1.00000E-30  BODY(345)= 1.00000E-30
  BODY(346)= 1.00000E-30  BODY(347)= 1.00000E-30  BODY(348)= 1.00000E-30  BODY(349)= 1.00000E-30  BODY(350)= 1.00000E-30
  BODY(351)= 1.00000E-30  BODY(352)= 1.00000E-30  BODY(353)= 1.00000E-30  BODY(354)= 1.00000E-30  BODY(355)= 1.00000E-30
  BODY(356)= 1.00000E-30  BODY(357)= 1.00000E-30  BODY(358)= 1.00000E-30  BODY(359)= 1.00000E-30  BODY(360)= 1.00000E-30
  BODY(361)= 1.00000E-30  BODY(362)= 1.00000E-30  BODY(363)= 1.00000E-30  BODY(364)= 1.00000E-30  BODY(365)= 1.00000E-30
  BODY(366)= 1.00000E-30  BODY(367)= 1.00000E-30  BODY(368)= 1.00000E-30  BODY(369)= 1.00000E-30  BODY(370)= 1.00000E-30
  BODY(371)= 1.00000E-30  BODY(372)= 1.00000E-30  BODY(373)= 1.00000E-30  BODY(374)= 1.00000E-30  BODY(375)= 1.00000E-30
  BODY(376)= 1.00000E-30  BODY(377)= 1.00000E-30  BODY(378)= 1.00000E-30  BODY(379)= 1.00000E-30  BODY(380)= 1.00000E-30
  BODY(381)= 1.00000E-30  BODY(382)= 1.00000E-30  BODY(383)= 1.00000E-30  BODY(384)= 1.00000E-30  BODY(385)= 1.00000E-30
  BODY(386)= 1.00000E-30  BODY(387)= 1.00000E-30  BODY(388)= 1.00000E-30  BODY(389)= 1.00000E-30  BODY(390)= 1.00000E-30
  BODY(391)= 1.00000E-30  BODY(392)= 1.00000E-30  BODY(393)= 1.00000E-30  BODY(394)= 1.00000E-30  BODY(395)= 1.00000E-30
  BODY(396)= 1.00000E-30  BODY(397)= 1.00000E-30  BODY(398)= 1.00000E-30  BODY(399)= 1.00000E-30  BODY(400)= 1.00000E-30
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                 APPROXIMATE AXISYMMETRIC BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 1
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600                                                    4.2800E+06             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    0.023   -0.021   -0.0205  -0.023    0.021    0.895    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   -4.0    0.022   -0.014   -0.0137  -0.015    0.021    0.898    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   -2.0    0.021   -0.007   -0.0068  -0.008    0.021    0.899    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
    0.0    0.021    0.000    0.0000   0.000    0.021   ******    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
    2.0    0.021    0.007    0.0068   0.008    0.021    0.899    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
    4.0    0.022    0.014    0.0137   0.015    0.021    0.898    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
    8.0    0.025    0.027    0.0273   0.031    0.021    0.892    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   12.0    0.029    0.041    0.0410   0.046    0.020    0.883    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   16.0    0.036    0.055    0.0546   0.063    0.019    0.871    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   20.0    0.044    0.069    0.0683   0.080    0.018    0.857    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   24.0    0.054    0.082    0.0820   0.097    0.016    0.842    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $BODY ZU(1) = -.595,-.476,-.372,-.138,.200,.334,.343,.343,.343,.343,           
        ZL(1) = -.595,-.715,-.754,-.805,-.868,-.868,-.868,-.868,-.868,-.868,     
  $END                                                                           
 CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION,EXAMPLE PROBLEM 1,CASE 2             
 SAVE                                                                            
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                   ASYMMETRIC (CAMBERED) BODY SOLUTION,EXAMPLE PROBLEM 1,CASE 2
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600                                                    4.2800E+06             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    0.022   -0.012   -0.0237  -0.014    0.021    1.638    3.227E-03    4.077E-03   -3.227E-03   -2.363E-03    0.000E+00
   -4.0    0.021   -0.007   -0.0156  -0.008    0.021    1.935    2.837E-03    4.059E-03   -2.837E-03   -2.352E-03    0.000E+00
   -2.0    0.021   -0.001   -0.0074  -0.002    0.021    4.616    2.859E-03    4.073E-03   -2.859E-03   -2.360E-03    0.000E+00
    0.0    0.021    0.005    0.0007   0.005    0.021    0.145    2.853E-03    4.069E-03   -2.853E-03   -2.357E-03    0.000E+00
    2.0    0.021    0.011    0.0088   0.011    0.021    0.783    2.818E-03    4.044E-03   -2.818E-03   -2.343E-03    0.000E+00
    4.0    0.022    0.016    0.0169   0.018    0.021    0.957    2.751E-03    3.996E-03   -2.751E-03   -2.315E-03    0.000E+00
    8.0    0.026    0.027    0.0326   0.030    0.022    1.084    2.537E-03    3.843E-03   -2.537E-03   -2.227E-03    0.000E+00
   12.0    0.031    0.036    0.0476   0.042    0.022    1.135    2.233E-03    3.622E-03   -2.233E-03   -2.098E-03    0.000E+00
   16.0    0.037    0.045    0.0616   0.053    0.023    1.161    3.100E-03    3.701E-03   -3.100E-03   -2.144E-03    0.000E+00
   20.0    0.048    0.061    0.0772   0.074    0.024    1.045    6.089E-03    4.404E-03   -6.089E-03   -2.552E-03    0.000E+00
   24.0    0.070    0.093    0.0968   0.114    0.026    0.852    9.984E-03    5.396E-03   -9.984E-03   -3.127E-03    0.000E+00
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON                                                                        
   NMACH = 3.0,                                                                  
   MACH(1) = 0.9,1.4,2.5,                                                        
   RNNUB = 6.4E6,9.96E6,17.0E6,                                                  
  $END                                                                           
 SAVE                                                                            
 CASEID ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3           
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                  ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.900                                                    6.4000E+06             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    NDM      NDM       NDM     NDM      NDM      0.995    3.433E-03    3.415E-03   -3.433E-03   -1.979E-03    0.000E+00
   -4.0    NDM                                                                                                       0.000E+00
   -2.0    NDM                                                                                                       0.000E+00
    0.0    NDM                                                                                                       0.000E+00
    2.0    NDM                                                                                                       0.000E+00
    4.0    NDM                                                                                                       0.000E+00
    8.0    NDM                                                                                                       0.000E+00
   12.0    NDM                                                                                                       0.000E+00
   16.0    NDM                                                                                                       0.000E+00
   20.0    NDM                                                                                                       0.000E+00
   24.0    NDM                                                                                                       0.000E+00
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                             CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
                                                   DATCOM BODY ALONE CONFIGURATION
                                  ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.900                                                    6.4000E+06             8.850      2.480     4.280     4.140    -0.200


                                                       BASIC BODY PROPERTIES

            WETTED AREA      XCG     ZCG     BASE AREA     ZERO LIFT DRAG   BASE DRAG   FRICTION DRAG   PRESSURE DRAG
             0.1837E+02     4.14   -0.20       1.0320           NDM           NDM           NDM             NDM 
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                  ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 1.400                                                    9.9600E+06             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    0.041   -0.034   -0.0260  -0.039    0.037    0.675    7.070E-03    4.588E-03   -7.070E-03   -2.658E-03    0.000E+00
   -4.0    0.039   -0.021   -0.0170  -0.024    0.037    0.712    6.202E-03    4.425E-03   -6.202E-03   -2.564E-03    0.000E+00
   -2.0    0.038   -0.010   -0.0083  -0.011    0.037    0.756    5.305E-03    4.249E-03   -5.305E-03   -2.462E-03    0.000E+00
    0.0    0.037    0.000    0.0000   0.000    0.037   ******    4.842E-03    4.156E-03   -4.842E-03   -2.408E-03    0.000E+00
    2.0    0.038    0.010    0.0083   0.011    0.037    0.756    5.305E-03    4.249E-03   -5.305E-03   -2.462E-03    0.000E+00
    4.0    0.039    0.021    0.0170   0.024    0.037    0.712    6.191E-03    4.420E-03   -6.191E-03   -2.561E-03    0.000E+00
    8.0    0.044    0.049    0.0353   0.055    0.037    0.642    7.795E-03    4.696E-03   -7.795E-03   -2.721E-03    0.000E+00
   12.0    0.054    0.084    0.0546   0.093    0.036    0.587    9.347E-03    4.933E-03   -9.347E-03   -2.858E-03    0.000E+00
   16.0    0.071    0.124    0.0748   0.139    0.034    0.538    1.110E-02    5.205E-03   -1.110E-02   -3.016E-03    0.000E+00
   20.0    0.098    0.172    0.0962   0.195    0.033    0.492    1.318E-02    5.569E-03   -1.318E-02   -3.227E-03    0.000E+00
   24.0    0.136    0.230    0.1193   0.265    0.031    0.450    1.542E-02    5.987E-03   -1.542E-02   -3.469E-03    0.000E+00
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                  ASYMMETRIC (CAMBERED) BODY SOLUTION, EXAMPLE PROBLEM 1, CASE 3
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 2.500                                                    1.7000E+07             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    0.027   -0.039   -0.0223  -0.041    0.023    0.537    7.792E-03    3.976E-03   -7.792E-03   -2.304E-03    0.000E+00
   -4.0    0.024   -0.024   -0.0145  -0.026    0.023    0.562    6.925E-03    3.803E-03   -6.925E-03   -2.204E-03    0.000E+00
   -2.0    0.023   -0.011   -0.0071  -0.012    0.023    0.590    6.032E-03    3.621E-03   -6.032E-03   -2.098E-03    0.000E+00
    0.0    0.023    0.000    0.0000   0.000    0.023   ******    5.572E-03    3.526E-03   -5.572E-03   -2.043E-03    0.000E+00
    2.0    0.023    0.011    0.0071   0.012    0.023    0.590    6.032E-03    3.621E-03   -6.032E-03   -2.098E-03    0.000E+00
    4.0    0.024    0.024    0.0145   0.026    0.023    0.562    6.943E-03    3.806E-03   -6.943E-03   -2.205E-03    0.000E+00
    8.0    0.030    0.056    0.0304   0.059    0.022    0.514    9.088E-03    4.233E-03   -9.088E-03   -2.453E-03    0.000E+00
   12.0    0.043    0.097    0.0484   0.104    0.022    0.467    1.231E-02    4.900E-03   -1.231E-02   -2.839E-03    0.000E+00
   16.0    0.066    0.154    0.0696   0.166    0.021    0.419    1.513E-02    5.504E-03   -1.513E-02   -3.189E-03    0.000E+00
   20.0    0.101    0.218    0.0924   0.239    0.020    0.386    1.524E-02    5.531E-03   -1.524E-02   -3.205E-03    0.000E+00
   24.0    0.144    0.276    0.1139   0.310    0.019    0.367    1.378E-02    5.211E-03   -1.378E-02   -3.019E-03    0.000E+00
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON                                                                        
   NMACH = 1.0,                                                                  
   MACH(1) = 2.5,                                                                
   RNNUB = 17.86E6,                                                              
   HYPERS = .TRUE.,                                                              
  $END                                                                           
  $BODY                                                                          
   DS = 0.0,                                                                     
  $END                                                                           
 CASEID HYPERSONIC BODY SOLUTION,  EXAMPLE PROBLEM 1, CASE 4                     
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                       HYPERSONIC BODY SOLUTION,  EXAMPLE PROBLEM 1, CASE 4
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 2.500                                                    1.7860E+07             8.850      2.480     4.280     4.140    -0.200
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -6.0    0.016   -0.020   -0.0202  -0.022    0.014    0.915    4.413E-03    3.348E-03   -4.413E-03   -1.940E-03    0.000E+00
   -4.0    0.014   -0.012   -0.0135  -0.013    0.013    1.014    3.744E-03    3.351E-03   -3.744E-03   -1.942E-03    0.000E+00
   -2.0    0.013   -0.005   -0.0067  -0.006    0.013    1.135    3.075E-03    3.363E-03   -3.075E-03   -1.949E-03    0.000E+00
    0.0    0.013   -0.000   -0.0000  -0.000    0.013    0.625    2.741E-03    3.373E-03   -2.741E-03   -1.954E-03    0.000E+00
    2.0    0.013    0.005    0.0067   0.006    0.013    1.135    3.075E-03    3.363E-03   -3.075E-03   -1.949E-03    0.000E+00
    4.0    0.014    0.012    0.0135   0.013    0.013    1.014    3.736E-03    3.349E-03   -3.736E-03   -1.940E-03    0.000E+00
    8.0    0.019    0.030    0.0268   0.032    0.014    0.834    4.961E-03    3.319E-03   -4.961E-03   -1.923E-03    0.000E+00
   12.0    0.027    0.052    0.0400   0.056    0.016    0.708    6.037E-03    3.324E-03   -6.037E-03   -1.926E-03    0.000E+00
   16.0    0.041    0.078    0.0534   0.086    0.018    0.619    6.927E-03    3.400E-03   -6.927E-03   -1.970E-03    0.000E+00
   20.0    0.060    0.107    0.0672   0.121    0.020    0.553    7.539E-03    3.496E-03   -7.539E-03   -2.026E-03    0.000E+00
   24.0    0.086    0.138    0.0814   0.161    0.022    0.504    7.992E-03    3.593E-03   -7.992E-03   -2.082E-03    0.000E+00
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.

 

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DATCOM 모델을 구축하는 방법은 매우 혼란스러울 수 있다. 여기에는 어떤 포인트를 클릭하는 인터페이스가 없으며, 공간 안에서 점들만 있을 뿐이다. 이 튜토리얼은 초보 사용자가 간단한 DATCOM 모델을 구축하고 시험하는 데 도움을 주려고 작성되었다. 얻은 수치는 정확하지 않을 수 있지만, 모델은 몇 가지 가정 제외하고는 비교적 정확해야 한다.
 
 
미코얀-구레비치 MiG-17
 

Mikoyan-Gurevich MiG-17

 
1949년, 미코얀-구레비치(MiG) 설계국은 MiG-15를 대체할 새로운 전투기 개발에 착수했다. 이 항공기의 두 가지 주요 특징은 더 얇고 경사각이 큰 날개와 안정성과 조종 성능을 향상시키려고 재설계된 꼬리 부분으로, 마하 1(음속)에 가까운 속도에서도 우수한 성능을 발휘했다. MiG-15와 외관상 유사하지만, MiG-17은 더 급격히 뒤로 굽은 날개, 애프터버너, 우수한 속도와 조종 특성을 갖추고 있으며 약 3피트 더 길다. 항공기 날개는 중간에 위치하며 뒤로 굽고 뾰족한 끝부분으로 좁아진다. 날개 베이스는 더 넓다. 엔진은 기체 내부에 위치한 터보제트 엔진으로, 코 부분에 원형 공기 흡입구를 가지고 있으며 하나의 작은 배기구를 가지고 있다. 기체는 짧고 두꺼운 시가 모양으로 뒤로 좁아지며, 둔탁한 코와 거품 모양의 조종석을 가지고 있다. 꼬리 날개는 뒤로 굽어지고 좁아지며 둥근 끝을 가지고 있다. 꼬리 날개는 뒤로 굽어지고 좁아진 플랫이 위쪽에 장착되었으며, 플랫과 꼬리 날개는 배기구를 덮고 있다.
 (GlobalSecurity.org)
 
MiG-17은 이 튜토리얼에 선택된 이유는 단순한 설계 때문이다. 기체 단면은 거의 원형이며(원형으로 가정됨), 날개 모양은 복잡하지 않으며, 꼬리 부분도 복잡하지 않다.
 
도면 및 치수

Figure 1: MiG 17 Views

 
이 프로젝트에서 가장 어려운 부분은 항공기의 정확한 측정을 제공할 수 있는 적절한 도면을 찾는 것이었다. 결국 여기 그림과 유사한 3면도 도면을 발견했다. MIG-17의 날개폭이 약 31피트 7인치이고, 길이가 36피트 5인치라는 사실을 활용하여 도면을 축척하고 필요한 치수를 얻을 수 있었다.
 
온라인에서 확인할 수 있듯이, 날개와 수평 꼬리의 후퇴각(sweep)은 약 45도이다. 대형 수직 꼬리날개의 후퇴각은 55도로 추정되나, 실제 값과 다를 수 있다. 날개의 이면각(dihedral)은 -3도이며, 경사각(incidence)은 1도이다.
 
앞서 언급했듯이, 기체 단면은 편리하게 원형이며, 여러 지점에서 일정하다. 참고로, 튜토리얼에서는 캐노피가 구현되지 않았으며, 이는 결과에 영향을 미쳤을 수 있지만 중요하지는 않다. 그러나 이 프로젝트의 주요 장애물은 공기역학 형상이다. MIG는 TsAGI S-12(12%) 공기역학 형상을 사용한다. 비행기는 날개 없이 비행할 수 없으며, 공기역학 형상은 비행에 큰 영향을 미치기 때문에 공기역학 형상의 선택은 매우 중요하다. 또한 Digital Datcom은 러시아 공기역학 형상을 고려하지 않기 때문에, TsAGI S-12(12%)가 NACA 66-012와 동일하다고 가정했다. 하지만 근거는 없다. (온라인에서 확인되지 않은 정보 제외). TsAGI 공기역학 형상의 데이터가 쉽게 구할 수 없기 때문에 DATCOM에 수동으로 입력할 수 없으며, 따라서 가정할 수밖에 없다.

입력 파일 작성
 
Digital DATCOM 매뉴얼 제1권 제3장(입력 정의)을 읽어보는 것이 좋다. 특히 3.1절과 3.2절을 참고하여 다음 내용에 익숙해지기 바란다. for005 파일(즉, 입력 파일)은 항공기의 비행 특성 및 기하학적 구조를 정의한다. 이 파일은 매우 특정한 형식을 따르며, 형식에서 벗어나는 경우 분석이 실행되지 않는다. 먼저 첫 번째 줄에 CASEID를 입력합니다:

CASEID MIKOYAN-GUREVICH MiG-17

 항공기의 비행 특성 및 기하 특성을 정의하는 모든 데이터는 namelists에 포함되어 있다. 입력 파일에서 namelists는 “$” 기호로 시작되며 (예: $FLTCON), 각 문장은 “$” 기호로 종료된다. 이 연습에서는 다음 namelists를 사용할 것이다:

  • FLTCON - 비행 조건 정의
  • SYNTHS - 기준선(referenceline)에 대해 중력 중심(cg), 날개, 수평 꼬리, 수직 꼬리의 위치를 결정
  • BODY - 기체 형상 정의
  • WGPLNF - 날개 형상 기하 정의
  • HTPLNF - 수평 꼬리 기하 정의
  • VTPLNF - 수직 꼬리 기하 정의

 
FLTCON 명령어
 
FLTCON 이름 목록은 분석할 비행 조건(마하 수, 고도, 공격 각도 등)을 정의한다. 입력 항목의 전체 목록은 디지털 데이터콤 매뉴얼 제1권 27페이지에 수록되어 있다. FLTCON 이름 목록에서 다음과 같은 변수를 사용할 것이다:

  • NMACH - 실행할 마하 수의 개수. 여기서는 단일 마하 수만 실행
  • MACH - 위에서 언급된 실행할 마하 수. 마하 = 0.60에서만 실행
  • NALPHA - 테스트할 받음각 수. 10개의 받음각에서 시험
  • ALSCHD - 받음각 시퀀스. (도 단위) -4, -2, 0, 2, 4, 6, 8, 10, 12, 14 (총 10개)
  • NALT - 실행할 고도 수. 단일 고도만 사용
  • ALT - 실행할 고도. 5000 피트만 사용
  • WT - 항공기의 중량. 13,395 파운드를 사용
  • LOOP - 1로 설정. LOOP 매개변수의 중요성은 추후 논의

이 변수는 FLTCON 이름 목록에 입력할 수 있다. 각 숫자에는 소수점이 반드시 포함되어야 한다. 또한 파일의 수평 길이는 특정 문자 수를 초과할 수 없으므로 주의하자. 변수 입력 순서는 중요하지 않지만, 다음 형식을 권장한다. 다음은 입력 파일에 포함하는 내용을 설명한다:

$FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,
0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,
WT=13395.0,LOOP=1.$

 
 
SYNTHS 명령어
 
SYNTHS(합성) 명령어는 매우 중요하다. 왜냐하면 이 목록은 무게중심(c.g.)의 위치뿐만 아니라 날개와 꼬리 표면의 위치를 설정하기 때문이다. 따라서 이 시점에서 항공기의 크기를 충분히 이해해야 한다. Datcom Volume I의 33쪽에는 필요한 차원이 정확히 표시되어 있다.
 
모든 수평 측정은 항공기의 노즈에서 측정한다. 모든 수직 측정은 항공기의 중심에 편리하게 배치된 기준선에서 측정한다. SYNTHS 이름 목록에서 다음 변수를 사용한다:

  • XCG - 무게 중심(c.g.)의 수평 위치. 무게 중심의 위치 정보가 주어지지 않았기 때문에, 무게중심 위치로 11.17 피트를 임의로 선택하였다(아마도 정확하지 않을 것이다).
  • ZCG - 무게 중심(c.g.)의 수직 위치(참조 선에 대한). 임의로 0 피트로 선택
  • XW - 날개 끝점의 수평 위치. 3.63 피트로 측정
  • ZW - 날개 끝점의 수직 위치(기준선 대비). 0.42 피트로 측정
  • ALIW - 날개 각도(Degree). MiG의 경우 1도
  • XH - 수평 꼬리 날개 끝점의 수평 위치. 28.73 피트로 측정
  • ZH - 수평 꼬리 날개 끝점의 수직 위치(기준선 대비). 5.24 피트로 측정
  • ALIH - 수평 꼬리 날개 각도. MiG에 대한 데이터가 없으므로 0도로 가정
  • XV - 수직 꼬리날개 정점의 수평 위치. 18.3 피트로 측정
  • ZV - 수직 꼬리날개 정점의 수직 위치(기준선 대비). 이 위치는 기준선에 있으므로 0 피트

이 숫자들은 SYNTHS 명령어에 입력할 수 있다:

$SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,
ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$

 
다음 도면은 이 명령어 및 이후의 명령어에서 사용할 차원을 표시한다.
 

그림 2: 미그기의 오른쪽 정면도
그림 3: 미그기의 평면도

 
BODY 명령어
 
이제 구성 요소를 모델링하기 시작할 수 있다. 먼저 기체부터 시작한다. 앞서 언급했듯이 캐노피는 무시하고, 각 스테이션에서 원형 단면을 가진 기체를 모델링할 것이다. 위 그림에서 볼 수 있듯이, 기체는 코 부분부터 시작해 후방 부분까지 8개의 스테이션으로 나뉘어져 있다. 각 스테이션에서 코 부분으로부터의 수평 거리와 각 스테이션의 단면적은 아래 표에 정리하였다:

스테이션 1 2 3 4 5 6 7 8
X (피트) 0.0 0.74 8.35 13.14 19.35 24.41 28.41 30.77
R (반경, 피트) 1.29 1.72 2.32 2.32 2.25 1.88 1.36 0.69
S (면적, 제곱 피트) 5.19 9.32 16.89 16.89 15.94 11.12 5.85 2.5

 
명령어 BODY에서 사용할 변수는 다음과 같다:

  • NX - 기체 스테이션 수
  • X - 각 스테이션의 수평 거리
  • S - 각 스테이션의 단면적
  • (기술적으로 “R”을 “S” 대신 사용할 수 있지만, 나중에 문제가 발생할 수 있다)

이 모든 값을 알고 있으면 기체를 완전히 정의할 수 있다. 데이터는 다음과 같이 입력한다.

$BODY NX=8.0,
X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,
S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$



WGPLNF 명령어
 
이제 WGPLNF 이름 목록을 사용하여 날개 형상을 정의할 수 있다. Datcom 제1권 37쪽과 38쪽은 모든 형상 정의에 매우 유용하다. 위의 도면은 날개 형상의 모양을 완전히 정의한다. 날개를 정의하는 데 사용할 변수들은 다음과 같다:

  • CHRDTP - 날개 끝 부분의 현의 길이. 7.02 피트로 측정
  • SSPNOP - 도면에서 “b*o/2”로 표시된 '반 스팬 외부 패널'이다. 날개가 두 부분으로 구성되어 있으면(예: MiG) 내부 패널과 외부 패널이 있다. 이 치수는 두 패널의 경계선에서 날개 끝 코드까지 측정한다. 측정 결과 11.32 피트이다.
  • SSPNE - '노출된' 반폭으로, 'b*/2'이다. 이 치수는 기체 측면에서 날개 끝 코드까지 측정한다. 측정 결과 13.41 피트이다.
  • SSPN - 이론적 반스팬으로, b/2입니다. 이 치수는 연결 코드에서 끝 코드까지 측정한다. 측정 결과 15.71 피트이다.
  • CHRDBP - 내측 패널과 외측 패널 사이의 분할점에서 코드(도면상의 “cb”). 측정 결과 8.4 피트이다.
  • CHRDR - 날개 연결부의 코드 길이. 측정 결과 14.0 피트입니다.
  • SAVSI - 내측 패널에서 날개 스윙 각도(매뉴얼 참조). MiG의 경우 내측과 외측 패널 간 스윙 각도가 다르지만, 이 값을 일정하게 유지하여 45도로 설정한다.
  • SAVSO - 날개 외측 패널의 날개 곡률. 앞서 언급된 대로 45도로 설정한다.
  • TWISTA - 날개 비틀림 각도(워시아웃). MiG는 0도이다.
  • CHSTAT - 곡률 각도를 참조하는 최대(mac)의 %. 일반적으로 c/4 또는 0.25이다.
  • DHDAHI - 내측 패널의 기수각. 내측과 외측 패널의 기수각이 동일(날개 전체에 걸쳐 일정한 기수각)인 경우 DHDADI만 입력한다. MiG의 경우 날개 기수각은 -3도이다.
  • TYPE - 다른 형상 유형(매뉴얼 참조). 1로 설정한.

이 값들은 다음과 같이 입력 파일에 입력한다:

$WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,
CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,
TWISTA=0.0,DHDADI=-3.0,TYPE=1.0$

 
 
HTPLNF 명령어
 
수평 꼬리 날개는 날개와 동일한 변수를 사용하여 동일한 방식으로 설정한다. 수평 꼬리 날개의 기하학적 구조가 더 단순하기 때문에, 우리는 다음 변수만 사용할 것이다: CHRDTP, SSPNE, SSPN, CHRDR, SAVSI, CHSTAT 및 TYPE.

  • CHRDTP는 1.86 피트
  • SSPNE는 5.42 피트
  • SSPN는 5.43 피트
  • CHRDR는 4.69 피트
  • SAVSI는 45 도
  • CHSTAT는 0.25
  • TYPE는 1

따라서 값들은 다음과 같이 HTPLNF 명령어에 입력한다:

$HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,
CHSTAT=0.25,TYPE=1.0$

 
VTPLNF 명령어
 
수직 꼬리날개는 날개와 동일한 변수를 사용하여 동일한 방식으로 설정한다. 수직 꼬리날개의 기하학적 구조가 더 단순하기 때문에, 다음과 같은 변수만 사용할 것이다: CHRDTP, SSPNE, SSPN, CHRDR, SAVSI, CHSTAT 및 TYPE.

  • CHRDTP는 3.76 피트
  • SSPNE는 6.05 피트
  • SSPN는 8.18 피트
  • CHRDR는 12.47 피트
  • SAVSI는 55 도 (측정하지 않았다.)
  • CHSTAT는 0.25
  • TYPE는 1

따라서 값들은 다음과 같이 VTPLNF 명령어에 입력한다:

$VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,
CHSTAT=0.25,TYPE=1.0$

 
 
에어포일 형상 설정
 
날개와 꼬리 부분의 공기역학 형상을 입력하는 것을 잊지 말아야 한다. 제1권 74페이지와 75페이지에 정보가 있다. 만약 날개가 NACA-2412 형상이라면, for005 파일에 다음과 같이 입력한다: NACAW-4-2412. 'NACA'는 DATCOM에 내장된 데이터가 있는 NACA 에어포일을 나타낸다. 'W'는 공기형상이 날개에 적용된다는 걸 의미한다(HT는 수평날개, VT는 수직날개). '4'는 4 시리즈 에어포일을 나타내며(DATCOM은 1, 4, 5, 6 시리즈 에어포일을 지원), 그 다음은 에어포일 지정 번호로, 이 예시에서는 '2412'이다.
 
MiG에서는 날개에 NACA 66-012 에어포일을 사용하며, 꼬리 부분에 66-009를 사용한다. 이들은 다음과 같이 DATCOM에 입력한다:

NACA-W-6-66-012 
NACA-H-6-66-009 
NACA-V-6-66-009

 
 
파일 종료
 
파일 끝에 정보를 지정하고, 추가 데이터를 제공할 때 사용할 수 있는 여러 명령어가 있다. 여기에서는 3개의 명령어를 사용한다:

  • DIM FT - 모든 치수가 피트 단위로 지정되며, 모든 출력은 '미국' 단위로 표시한다.
  • BUILD - 모든 구성 요소의 데이터를 표시한다. 항공기만 표시하지 않는다.
  • PLOT - 플로팅 프로그램에 입력하기 위한 플롯 파일(for013.dat)을 만든다.

마지막으로, 파일은 “NEXT CASE”로 끝난다. 입력 파일에서 다음과 같이 표시한다:

DIM FT
BUILD
PLOT
NEXT CASE


전체 입력 파일
 
다음은 DATCOM에서 실행될 전체 입력 파일이다.

CASEID ----- MIKOYAN-GUREVICH MiG-17 -----
 $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,
  0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,
  WT=13395.0,LOOP=1.$
 $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,
  ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$
 $OPTINS SREF=243.0$
 $BODY NX=8.0,
  X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,
  S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$
NACA-W-6-66-012
 $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,
  CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,
  TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$
NACA-H-6-66-009
 $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,
  CHSTAT=0.25,TYPE=1.0$
NACA-V-6-66-009
 $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,
  CHSTAT=0.25,TYPE=1.0$
DIM FT
BUILD
PLOT
NEXT CASE

 

 
 
출력 파일

  ****************************************************
  *    USAF STABILITY AND CONTROL  DIGITAL DATCOM    *
  *    PROGRAM REV. JAN 96   DIRECT INQUIRIES TO:    *
  *    WRIGHT LABORATORY  (WL/FIGC)  ATTN: W. BLAKE  *
  *      WRIGHT PATTERSON AFB, OHIO  45433           *
  *    PHONE (513) 255-6764,   FAX (513) 258-4054    *
  ****************************************************
1                         CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0******************************  INPUT DATA CARDS  ******************************

 CASEID ----- MIKOYAN-GUREVICH MiG-17 -----                                      
  $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,                 
   0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,                    
   WT=13395.0,LOOP=1.$                                                           
  $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,                   
   ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$                                              
  $OPTINS SREF=243.0$                                                            
  $BODY NX=8.0,                                                                  
   X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,                             
   S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$                              
 NACA-W-6-66-012                                                                 
  $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,                       
   CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,                      
   TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$                                  
 NACA-H-6-66-009                                                                 
  $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,                
   CHSTAT=0.25,TYPE=1.0$                                                         
 NACA-V-6-66-009                                                                 
  $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,               
   CHSTAT=0.25,TYPE=1.0$                                                         
 DIM FT                                                                          
 BUILD                                                                           
 PLOT                                                                            
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
 CASEID ----- MIKOYAN-GUREVICH MiG-17 -----                                      
  $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,                 
   0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,                    
   WT=13395.0,LOOP=1.$                                                           
  $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,                   
   ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$                                              
  $OPTINS SREF=243.0$                                                            
  $BODY NX=8.0,                                                                  
   X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,                             
   S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$                              
 NACA-W-6-66-012                                                                 
  $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,                       
   CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,                      
   TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$                                  
 NACA-H-6-66-009                                                                 
  $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,                
   CHSTAT=0.25,TYPE=1.0$                                                         
 NACA-V-6-66-009                                                                 
  $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,               
   CHSTAT=0.25,TYPE=1.0$                                                         
 DIM FT                                                                          
 BUILD                                                                           
 PLOT                                                                            
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                        WING SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09699 /DEG.

                                    LEADING EDGE RADIUS =   0.00993 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.12000 FRACTION CHORD

                                                DELTA-Y =   2.01961 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.11881 /DEG.      XAC =   0.26851
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                   HORIZONTAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09870 /DEG.

                                    LEADING EDGE RADIUS =   0.00559 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.09000 FRACTION CHORD

                                                DELTA-Y =   1.52747 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.12143 /DEG.      XAC =   0.26444
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                    VERTICAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09870 /DEG.

                                    LEADING EDGE RADIUS =   0.00559 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.09000 FRACTION CHORD

                                                DELTA-Y =   1.52747 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.12143 /DEG.      XAC =   0.26444
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.006   -0.003   -0.0151  -0.004    0.005    3.976    8.326E-04    3.835E-03   -8.326E-04   -1.106E-03    0.000E+00
   -2.0    0.005   -0.002   -0.0076  -0.002    0.005    4.063    8.580E-04    3.784E-03   -8.580E-04   -1.092E-03    0.000E+00
    0.0    0.005    0.000    0.0000   0.000    0.005   ******    8.453E-04    3.810E-03   -8.453E-04   -1.099E-03    0.000E+00
    2.0    0.005    0.002    0.0076   0.002    0.005    4.063    8.580E-04    3.784E-03   -8.580E-04   -1.092E-03    0.000E+00
    4.0    0.006    0.003    0.0151   0.004    0.005    3.976    8.832E-04    3.734E-03   -8.832E-04   -1.077E-03    0.000E+00
    6.0    0.006    0.005    0.0226   0.006    0.005    3.887    9.082E-04    3.685E-03   -9.082E-04   -1.063E-03    0.000E+00
    8.0    0.006    0.007    0.0299   0.008    0.005    3.798    9.328E-04    3.636E-03   -9.328E-04   -1.049E-03    0.000E+00
   10.0    0.007    0.009    0.0371   0.010    0.005    3.709    9.569E-04    3.588E-03   -9.569E-04   -1.035E-03    0.000E+00
   12.0    0.008    0.011    0.0442   0.012    0.005    3.619    9.804E-04    3.541E-03   -9.804E-04   -1.022E-03    0.000E+00
   14.0    0.008    0.013    0.0513   0.015    0.005    3.530    1.004E-03    3.495E-03   -1.004E-03   -1.008E-03    0.000E+00
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                      WING ALONE CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.008   -0.141    0.0886  -0.141   -0.002   -0.629    4.578E-02   -2.828E-02   -2.768E-04    2.377E-05    1.160E-03
   -2.0    0.006   -0.046    0.0292  -0.046    0.004   -0.629    4.671E-02   -2.912E-02   -2.948E-04    2.562E-06    7.170E-04
    0.0    0.006    0.046   -0.0279   0.046    0.006   -0.603    4.671E-02   -2.853E-02   -2.948E-04    2.561E-06    2.837E-04
    2.0    0.008    0.141   -0.0849   0.141    0.003   -0.603    4.777E-02   -3.006E-02   -2.768E-04    2.375E-05   -1.595E-04
    4.0    0.013    0.237   -0.1481   0.238   -0.004   -0.623    4.861E-02   -3.303E-02   -2.378E-04    6.761E-05   -6.127E-04
    6.0    0.021    0.335   -0.2170   0.335   -0.015   -0.647    4.904E-02   -3.303E-02   -1.776E-04    1.350E-04   -1.072E-03
    8.0    0.031    0.433   -0.2802   0.433   -0.030   -0.646    4.798E-02   -2.921E-02   -9.633E-05    2.257E-04   -1.533E-03
   10.0    0.043    0.527   -0.3339   0.527   -0.049   -0.634    4.396E-02   -2.311E-02    3.331E-06    3.337E-04   -1.972E-03
   12.0    0.056    0.609   -0.3726   0.608   -0.072   -0.613    3.844E-02   -1.962E-02    1.083E-04    4.457E-04   -2.358E-03
   14.0    0.068    0.681   -0.4124   0.677   -0.098   -0.609    3.314E-02   -2.011E-02    2.138E-04    5.565E-04   -2.694E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                    HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.002   -0.032    0.0757  -0.032   -0.000   -2.349    8.325E-03   -1.965E-02    1.322E-06    2.767E-06    5.983E-05
   -2.0    0.001   -0.016    0.0371  -0.016    0.001   -2.343    8.044E-03   -1.892E-02    3.215E-07    6.678E-07    2.940E-05
    0.0    0.001    0.000    0.0000   0.000    0.001   ******    7.904E-03   -1.854E-02    0.000E+00    0.000E+00   -1.218E-36
    2.0    0.001    0.016   -0.0370   0.016    0.001   -2.339    8.044E-03   -1.887E-02    3.215E-07    6.677E-07   -2.940E-05
    4.0    0.002    0.032   -0.0755   0.032   -0.000   -2.343    8.289E-03   -1.953E-02    1.322E-06    2.767E-06   -5.983E-05
    6.0    0.003    0.049   -0.1152   0.049   -0.002   -2.351    8.461E-03   -2.009E-02    3.039E-06    6.409E-06   -9.105E-05
    8.0    0.004    0.066   -0.1559   0.066   -0.005   -2.363    8.558E-03   -2.057E-02    5.487E-06    1.166E-05   -1.228E-04
   10.0    0.006    0.083   -0.1974   0.083   -0.008   -2.378    8.377E-03   -2.050E-02    8.653E-06    1.852E-05   -1.547E-04
   12.0    0.008    0.100   -0.2378   0.099   -0.012   -2.400    7.411E-03   -1.865E-02    1.240E-05    2.652E-05   -1.851E-04
   14.0    0.011    0.113   -0.2720   0.112   -0.017   -2.428    5.900E-03   -1.551E-02    1.604E-05    3.411E-05   -2.098E-04
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                     VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.001    0.000    0.0000   0.000    NDM     ******    0.000E+00    0.000E+00   -7.955E-03    3.809E-03   -1.114E-03
   -2.0                                                                                                             -9.827E-04
    0.0                                                                                                             -8.503E-04
    2.0                                                                                                             -7.168E-04
    4.0                                                                                                             -5.825E-04
    6.0                                                                                                             -4.475E-04
    8.0                                                                                                             -3.119E-04
   10.0                                                                                                             -1.760E-04
   12.0                                                                                                             -3.980E-05
   14.0                                                                                                              9.641E-05
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                       WING-BODY CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.014   -0.199    0.0910  -0.199   -0.000   -0.456    6.394E-02   -3.075E-02   -1.194E-03   -1.190E-03    1.351E-03
   -2.0    0.011   -0.072    0.0307  -0.073    0.009   -0.422    6.263E-02   -2.953E-02                              7.584E-04
    0.0    0.011    0.052   -0.0272   0.052    0.011   -0.527    6.257E-02   -2.894E-02                              1.777E-04
    2.0    0.013    0.178   -0.0851   0.178    0.007   -0.477    6.387E-02   -3.071E-02                             -4.141E-04
    4.0    0.019    0.307   -0.1500   0.308   -0.003   -0.488    6.503E-02   -3.415E-02                             -1.019E-03
    6.0    0.027    0.438   -0.2217   0.438   -0.019   -0.506    6.566E-02   -3.434E-02                             -1.633E-03
    8.0    0.037    0.570   -0.2874   0.569   -0.042   -0.505    6.444E-02   -3.026E-02                             -2.250E-03
   10.0    0.050    0.696   -0.3427   0.694   -0.072   -0.494    5.945E-02   -2.354E-02                             -2.840E-03
   12.0    0.063    0.807   -0.3816   0.803   -0.106   -0.475    5.233E-02   -1.966E-02                             -3.364E-03
   14.0    0.077    0.905   -0.4214   0.897   -0.144   -0.470    4.531E-02   -2.017E-02                             -3.821E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                 BODY-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.007   -0.036    0.0605  -0.036    0.005   -1.674    9.241E-03   -1.556E-02   -3.717E-01   -1.190E-03    4.503E-05
   -2.0    0.007   -0.018    0.0300  -0.018    0.006   -1.686    8.934E-03   -1.499E-02                              2.038E-05
    0.0    0.006    0.000    0.0006   0.000    0.006   ******    8.780E-03   -1.480E-02                             -3.429E-06
    2.0    0.007    0.018   -0.0292   0.018    0.006   -1.643    8.934E-03   -1.537E-02                             -2.724E-05
    4.0    0.007    0.036   -0.0609   0.036    0.005   -1.684    9.205E-03   -1.629E-02                             -5.189E-05
    6.0    0.009    0.054   -0.0944   0.055    0.003   -1.716    9.402E-03   -1.713E-02                             -7.717E-05
    8.0    0.011    0.073   -0.1294   0.074    0.000   -1.747    9.524E-03   -1.787E-02                             -1.029E-04
   10.0    0.013    0.092   -0.1659   0.093   -0.003   -1.777    9.363E-03   -1.806E-02                             -1.288E-04
   12.0    0.016    0.111   -0.2017   0.112   -0.007   -1.805    8.414E-03   -1.642E-02                             -1.537E-04
   14.0    0.019    0.126   -0.2315   0.127   -0.012   -1.823    6.920E-03   -1.346E-02                             -1.745E-04
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                  BODY-VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.006   -0.003   -0.0151  -0.004    0.006    3.908    8.326E-04    3.835E-03   -8.788E-03    2.702E-03   -1.114E-03
   -2.0    0.006   -0.002   -0.0076  -0.002    0.006    3.992    8.580E-04    3.784E-03                             -9.827E-04
    0.0    0.006    0.000    0.0000   0.000    0.006   ******    8.453E-04    3.810E-03                             -8.503E-04
    2.0    0.006    0.002    0.0076   0.002    0.006    3.992    8.580E-04    3.784E-03                             -7.168E-04
    4.0    0.006    0.003    0.0151   0.004    0.006    3.908    8.832E-04    3.734E-03                             -5.825E-04
    6.0    0.007    0.005    0.0226   0.006    0.006    3.822    9.082E-04    3.685E-03                             -4.475E-04
    8.0    0.007    0.007    0.0299   0.008    0.006    3.736    9.328E-04    3.636E-03                             -3.119E-04
   10.0    0.008    0.009    0.0371   0.010    0.006    3.649    9.569E-04    3.588E-03                             -1.760E-04
   12.0    0.008    0.011    0.0442   0.012    0.006    3.562    9.804E-04    3.541E-03                             -3.980E-05
   14.0    0.009    0.013    0.0513   0.015    0.006    3.475    1.004E-03    3.495E-03                              9.641E-05
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                               WING-BODY-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.015   -0.219    0.1391  -0.220    0.000   -0.633    6.830E-02   -4.069E-02   -1.192E-03   -1.187E-03    1.411E-03
   -2.0    0.012   -0.084    0.0592  -0.085    0.009   -0.699    6.671E-02   -3.906E-02                              7.878E-04
    0.0    0.012    0.048   -0.0171   0.048    0.012   -0.360    6.638E-02   -3.789E-02                              1.777E-04
    2.0    0.015    0.181   -0.0924   0.182    0.008   -0.509    6.740E-02   -3.907E-02                             -4.435E-04
    4.0    0.020    0.317   -0.1734   0.318   -0.002   -0.546    6.830E-02   -4.193E-02                             -1.079E-03
    6.0    0.029    0.454   -0.2601   0.455   -0.019   -0.572    6.873E-02   -4.172E-02                             -1.724E-03
    8.0    0.041    0.592   -0.3403   0.592   -0.042   -0.575    6.744E-02   -3.754E-02                             -2.372E-03
   10.0    0.055    0.724   -0.4102   0.723   -0.072   -0.568    6.239E-02   -3.078E-02                             -2.995E-03
   12.0    0.070    0.842   -0.4634   0.838   -0.106   -0.553    5.526E-02   -2.697E-02                             -3.549E-03
   14.0    0.086    0.945   -0.5181   0.938   -0.146   -0.552    4.829E-02   -2.773E-02                             -4.031E-03
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -4.0      1.000     -1.454        0.479
                                     -2.0      1.000     -0.496        0.491
                                      0.0      1.000      0.510        0.520
                                      2.0      1.000      1.582        0.554
                                      4.0      1.000      2.726        0.589
                                      6.0      1.000      3.938        0.620
                                      8.0      1.000      5.207        0.634
                                     10.0      1.000      6.473        0.615
                                     12.0      1.000      7.669        0.590
                                     14.0      1.000      8.835        0.583
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                WING-BODY-VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.015   -0.199    0.0910  -0.199    0.001   -0.456    6.394E-02   -3.075E-02   -9.149E-03    2.619E-03    2.375E-04
   -2.0    0.012   -0.072    0.0307  -0.073    0.009   -0.422    6.263E-02   -2.953E-02                             -2.243E-04
    0.0    0.012    0.052   -0.0272   0.052    0.012   -0.527    6.257E-02   -2.894E-02                             -6.726E-04
    2.0    0.014    0.178   -0.0851   0.178    0.008   -0.477    6.387E-02   -3.071E-02                             -1.131E-03
    4.0    0.020    0.307   -0.1500   0.308   -0.002   -0.488    6.503E-02   -3.415E-02                             -1.602E-03
    6.0    0.027    0.438   -0.2217   0.439   -0.018   -0.506    6.566E-02   -3.434E-02                             -2.080E-03
    8.0    0.038    0.570   -0.2874   0.569   -0.041   -0.505    6.444E-02   -3.026E-02                             -2.562E-03
   10.0    0.051    0.696   -0.3427   0.694   -0.071   -0.494    5.945E-02   -2.354E-02                             -3.016E-03
   12.0    0.064    0.807   -0.3816   0.803   -0.105   -0.475    5.233E-02   -1.966E-02                             -3.404E-03
   14.0    0.078    0.905   -0.4214   0.897   -0.143   -0.470    4.531E-02   -2.017E-02                             -3.725E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.016   -0.219    0.1391  -0.220    0.001   -0.633    6.830E-02   -4.069E-02   -9.147E-03    2.622E-03    2.974E-04
   -2.0    0.013   -0.084    0.0592  -0.085    0.010   -0.699    6.671E-02   -3.906E-02                             -1.949E-04
    0.0    0.013    0.048   -0.0171   0.048    0.013   -0.360    6.638E-02   -3.789E-02                             -6.726E-04
    2.0    0.016    0.181   -0.0924   0.182    0.009   -0.509    6.740E-02   -3.907E-02                             -1.160E-03
    4.0    0.021    0.317   -0.1734   0.318   -0.001   -0.546    6.830E-02   -4.193E-02                             -1.662E-03
    6.0    0.030    0.454   -0.2601   0.455   -0.018   -0.572    6.873E-02   -4.172E-02                             -2.171E-03
    8.0    0.042    0.592   -0.3403   0.592   -0.041   -0.575    6.744E-02   -3.754E-02                             -2.684E-03
   10.0    0.056    0.724   -0.4102   0.723   -0.071   -0.568    6.239E-02   -3.078E-02                             -3.171E-03
   12.0    0.071    0.842   -0.4634   0.838   -0.106   -0.553    5.526E-02   -2.697E-02                             -3.589E-03
   14.0    0.087    0.945   -0.5181   0.938   -0.145   -0.552    4.829E-02   -2.773E-02                             -3.935E-03
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -4.0      1.000     -1.454        0.479
                                     -2.0      1.000     -0.496        0.491
                                      0.0      1.000      0.510        0.520
                                      2.0      1.000      1.582        0.554
                                      4.0      1.000      2.726        0.589
                                      6.0      1.000      3.938        0.620
                                      8.0      1.000      5.207        0.634
                                     10.0      1.000      6.473        0.615
                                     12.0      1.000      7.669        0.590
                                     14.0      1.000      8.835        0.583
0*** VEHICLE WEIGHT =  13395.00 LB.
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.12422
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.

 
 
for013.dat 파일

  1.0000E+00  1.0000E+01  6.0000E-01  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30 -4.0000E+00 -2.0000E+00  0.0000E+00  2.0000E+00  4.0000E+00  6.0000E+00  8.0000E+00  1.0000E+01
  1.2000E+01  1.4000E+01  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.7609E+03  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  6.0000E-01  1.4000E+00  0.0000E+00  5.0000E+03  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  5.0084E+02  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.3395E+04  1.0000E-30  1.0000E+00  1.0000E+00
  1.1170E+01  3.6300E+00  4.2000E-01  1.0000E+00  0.0000E+00  2.8730E+01  5.2400E+00  0.0000E+00  1.8300E+01  1.4013E-45
  1.0000E-30  1.0000E-30  1.0000E+00  0.0000E+00  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  2.4300E+02  9.0649E+00  1.6000E-04  3.1420E+01
  T  T  T  T  T  T  T  T  T  T  T  F  F  F  F  F  T  F  F  F  F  F  F  F  F  F  T  F  F  F  F  F  F  T
  5.5052E-03  5.3248E-03  5.2658E-03  5.3248E-03  5.5052E-03  5.8118E-03  6.2490E-03  6.8207E-03  7.5304E-03  8.3808E-03
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
 -3.4319E-03 -1.6906E-03  0.0000E+00  1.6906E-03  3.4319E-03  5.2234E-03  7.0645E-03  8.9544E-03  1.0892E-02  1.2876E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
 -1.5138E-02 -7.6191E-03  0.0000E+00  7.6191E-03  1.5138E-02  2.2556E-02  2.9876E-02  3.7098E-02  4.4226E-02  5.1261E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
 -3.8075E-03 -1.8754E-03  0.0000E+00  1.8754E-03  3.8075E-03  5.8023E-03  7.8654E-03  1.0003E-02  1.2220E-02  1.4521E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  5.2524E-03  5.2626E-03  5.2658E-03  5.2626E-03  5.2524E-03  5.2340E-03  5.2050E-03  5.1622E-03  5.1013E-03  5.0169E-03
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  8.3262E-04  8.5797E-04  8.4531E-04  8.5797E-04  8.8319E-04  9.0816E-04  9.3277E-04  9.5688E-04  9.8039E-04  1.0036E-03
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  3.8348E-03  3.7844E-03  3.8096E-03  3.7844E-03  3.7342E-03  3.6845E-03  3.6356E-03  3.5876E-03  3.5408E-03  3.4947E-03
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.3221E-06  3.2149E-07  0.0000E+00  3.2149E-07  1.3221E-06  3.0393E-06  5.4868E-06  8.6529E-06  1.2400E-05  1.6037E-05
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  2.7675E-06  6.6783E-07  0.0000E+00  6.6774E-07  2.7670E-06  6.4088E-06  1.1656E-05  1.8517E-05  2.6518E-05  3.4114E-05
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  7.3285E-03  6.5597E-03  6.3135E-03  6.5597E-03  7.3285E-03  8.6554E-03  1.0562E-02  1.3053E-02  1.5998E-02  1.8966E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  8.3262E-04  8.5797E-04  8.4531E-04  8.5797E-04  8.8319E-04  9.0816E-04  9.3277E-04  9.5688E-04  9.8039E-04  1.0036E-03
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.5480E-02  1.2279E-02  1.1989E-02  1.4567E-02  2.0182E-02  2.8836E-02  4.0666E-02  5.4856E-02  7.0045E-02  8.5653E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  6.8297E-02  6.6712E-02  6.6379E-02  6.7404E-02  6.8299E-02  6.8729E-02  6.7435E-02  6.2388E-02  5.5255E-02  4.8288E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.4590E-02  1.2008E-02  1.1949E-02  1.4410E-02  1.9557E-02  2.7485E-02  3.8200E-02  5.1010E-02  6.4425E-02  7.7838E-02
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  6.3941E-02  6.2633E-02  6.2567E-02  6.3866E-02  6.5033E-02  6.5659E-02  6.4443E-02  5.9450E-02  5.2332E-02  4.5307E-02
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.2634E-02

 
 
for014.dat 파일
 

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R

 
참고문헌
 
데이터와 역사
Mig-17의 청사진, http://www.the-blueprints.com
역사, http://www.globalsecurity.org/military/world/russia/mig-17.htm
역사와 데이터, http://www.vectorsite.net/avmig15_2.html
사진, http://www.suchoj.com/galerie/index.htm?http://www.suchoj.com/andere/MiG-17/galerie.shtml

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The method of building a model is DATCOM can be immensely confusing. There are no point-and-click interfaces here, only points in space. This tutorial aims at helping the novice user build a simple DATCOM model and test it. The numbers obtained may not be correct, but the model should be fairly accurate (except for a few assumptions).

 

 

THE MIKOYAN-GUREVICH MIG-17

 

Mikoyan-Gurevich MiG-17

 

In 1949, the Mikoyan-Gurevich (MiG) design bureau began work on a new fighter to replace the MiG-15. Two features of the aircraft were a thinner wing of greater sweep and a redesigned tail that improved stability and handling at speeds approaching Mach 1 (speed of sound). Although similar in appearance to the MiG-15, the MiG-17 has more sharply swept wings, an afterburner, better speed and handling characteristics and is about three feet longer. The wings of the aircraft are midmounted, swept-back, and tapered with blunt tips. They have wide wing roots. The engine is one turbojet inside the body and has a round air intake in the nose. It has a single, small exhaust. The fuselage is short, thick, cigar-shaped and tapered to the rear. It has a blunt nose and bubble canopy. The tail fin is swept-back and tapered with rounded tip. Flats are high-mounted on the tail fin, swept-back, and tapered. Flats and fin overhang the exhaust. (GlobalSecurity.org)

 

The MiG-17 was chosen for this tutorial because of its simple design. The fuselage cross-section is almost circular (and assumed to be), the wing shape is not complex, and the tails are not complex.

 

 

DRAWINGS AND DIMENSIONS

Figure 1: MiG 17 Views

 

The most difficult aspect of this project was finding adequate drawings of the aircraft which could provide accurate and consistent measurements. Eventually a drawing similar to the 3 view drawing pictured here was found. We can use the fact that MIG-17 has a wingspan of approximately 31 feet 7 inches and a length of 36 feet 5 inches to scale the drawing and get the dimensions needed.

 

It can be found (online) that the sweep of the wing and horizontal tail is 45 deg (approximately). The sweep of the large vertical tail is taken to be 55 deg, although it may not be. The dihedral of the wing is -3 deg and the incidence is 1 deg.

 

As stated before, the fuselage cross section is conveniently circular, and for several stations, constant. It should be noted that the canopy was not implemented in the tutorial, which could possibly have affected the results (unimportant though).A major hindrance of the project, however, is the airfoil. The MIG uses a TsAGI S-12 (12%) airfoil shape. Since planes don't fly without wings, and the airfoil shape has a profound impact on flight, the selection of the airfoil is critical. Furthermore, the Digital Datcom does not account for Russian airfoils, so the assumption that a TsAGI S-12 (12%) is equivalent to a NACA 66-012 was made. Justification: none (aside from unverified information online). Since the data for TsAGI airfoils are not readily available, the characteristics cannot be inputted manually into DATCOM, therefore we are left having to make this assumption.

 

WRITING THE for005.dat FILE

 

It would be wise to read section 3 (Definition of Inputs) of volume I of the Digital DATCOM manual, especially 3.1 and 3.2, to familiarize yourself for what is coming next.The for005 file (aka input file) defines the flight characteristics and geometry of the aircraft. It follows a very specific format and any deviance for the format will cause the analysis not to be run.First we input the CASEID on the first line: 

CASEID MIKOYAN-GUREVICH MiG-17

 

Every piece of data that defines the flight characteristics and geometry of the aircraft is contained in namelists. In the input file, namelists are preceded by a "$" sign (ex. $FLTCON) and the statements are terminated with "$" signs. For this exercise we will use the following namelists:

  • FLTCON - defines the flight conditions
  • SYNTHS - locates the cg, wing, horizontal tail, and vertical tail with respect to a referenceline
  • BODY - defines the body geometry
  • WGPLNF - defines the wing planform geometry
  • HTPLNF - defines the horizontal tail geometry
  • VTPLNF - defines the vertical tail geometry

 

THE FLTCON NAMELIST

 

The FLTCON namelist defines the flight conditions such as Mach number(s), altitude(s), and angle of attacks to be analyzed. A full list of the inputs can be found on page 27 of the Digital Datcom manual volume I. We will use the following variables from the FLTCON namelist:

  • NMACH - number of Mach numbers to be run. We will only run at one Mach.
  • MACH - the aformentioned Mach numbers to be run. We will run at Mach = 0.60.
  • NALPHA - the number of angles of attack to test. We will test at 10 AOA's.
  • ALSCHD - the schedule of angles of attack. We will use (in deg): -4, -2, 0, 2, 4, 6, 8, 10, 12, 14 (ten total)
  • NALT - number of altitudes to run. We will test only one altitude.
  • ALT - the altitudes to run. We will test at 5000 feet.
  • WT - the weight of the aircraft. We will use 13395 lbs for the MiG.
  • LOOP - we will set to 1. A discussion of the important LOOP parameter will be presented at some other time.

We can input these variables into the FLTCON namelist. Note that each number must contain a decimal point. Also, the file can only be a certain number of characters in horizontal length, so do not go over. The order in which the variables are given are not crucial, but the following format is recommended. The following describes what goes into the input file: 

$FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,
0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,
WT=13395.0,LOOP=1.$

 

 

THE SYNTHS NAMELIST

 

The SYNTHS (Synthesis) namelist is very important because it sets up the c.g. location as well as the position of the wing and tail surfaces. So at this point you should know the dimensions of the aircraft pretty well. Page 33 in Datcom Volume I indicates exactly what dimensions you will need.

 

All horizontal measurements will be taken from the nose of the aircraft. All vertical measurements will be taken from a reference line conveniently placed at the center of the aircraft. The following variables from the SYNTHS namelist will be used:

 

  • XCG - the horizontal position of the c.g. Since information of the c.g. position is not given, ac.g. position of 11.17 ft. was arbitrarily chosen (probably not right).
  • ZCG - the vertical position of the c.g. with respect to the reference line. Arbitrarily chosen as0 feet.
  • XW - the horizontal position of the apex of the wing. Measured as 3.63 feet.
  • ZW - the vertical position of the wing apex wrt the reference line. Measured as 0.42 feet.
  • ALIW - the incidence of the wing in degrees. For the MiG, this is 1 degree.
  • XH - the horizontal position of the apex of the horizontal tail. Measured as 28.73 feet.
  • ZH - the vertical position of the horiz. tail apex wrt the reference line. Measured as 5.24 feet.
  • ALIH - incidence of the horizontal tail. No data found for the MiG, so taken as 0 degrees.
  • XV - the horizontal position of the apex of the vertical tail. Measured as 18.3 feet.
  • ZV - the vertical position of the vertical tail apex wrt the reference line. Since this lies on thereference line, it is 0 feet.

These numbers can be inputted into the SYNTHS namelist:

$SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,
ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$

 

The following drawings will give the dimensions that will be used in this namelist and the subsequent ones.

 

Figure 2: Right Side View of MiG
Figure 3:Top View of MiG

 

THE BODY NAMELIST

 

Now we can start modeling the components. First, we'll start with the body. As stated previously, we will forget the canopy and model the fuselage as having a circular cross section at each station. Note that in the drawing above, we have 8 stations starting with the nose and concluding at the rear section of the fuselage. We will need the horizontal distance from the nose at each station (Xdistance) as well as the cross sectional area at each station. The numbers are tabulated below:

Station 1 2 3 4 5 6 7 8
X (feet) 0.0 0.74 8.35 13.14 19.35 24.41 28.41 30.77
R (radius, feet) 1.29 1.72 2.32 2.32 2.25 1.88 1.36 0.69
S (area, feet^2) 5.19 9.32 16.89 16.89 15.94 11.12 5.85 2.5

 

The variables of the namelist BODY that we will use are:

  • NX - number of body stations
  • X - horizontal distance of each station
  • S - cross sectional area at each station
  • (Technically we could use "R" instead of "S", but there are problems with that later on)

With all of these values know, we can fully define the fuselage. The data is inputted as follows

$BODY NX=8.0,
X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,
S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$

 

THE WGPLNF NAMELIST

 

Now we can define the wing planform using the WGPLNF namelist. Datcom volume I page 37 and 38 can be extremely helpful for all of the planforms. The drawings above fully prescribe the wing planform shape. The following are the variables we will use in defining the wing:

  • CHRDTP - the length of the chord at the tip of the wing. Measured to be 7.02 feet.
  • SSPNOP - the "Semi-Span outboard panel" which is "b*o/2" in the drawing. If the wing has two sections, like the MiG, there is an inboard panel and an outboard panel. This dimension is taken from the demarcation of the two panels to the tip chord. Measured to be 11.32 feet.
  • SSPNE - the "exposed" semi-span, which is the "b*/2". This dimension is from the side of the fuselage to the tip chord. Measured to be 13.41 feet..
  • SSPN - the theoretical semi-span, which is b/2. This dimension is from the root chord to the tip chord. Measured to be 15.71 feet.
  • CHRDBP - the chord at the break point between the inboard and outboard panel (the "cb" in the drawing). Measured to be 8.4 feet.
  • CHRDR - the length of the chord at the root of the wing. Measured to be 14.0 feet.
  • SAVSI - the sweep of the wing at the inboard panel (refer to the manual). Although the sweep of the MiG differs from the inboard to the outboard panel, we will take this as constant and keep it as 45 degrees.
  • SAVSO - the sweep of the wing at the outboard panel. A stated before, it will be 45 deg.
  • TWISTA - the twist angle of the wing (wash-out). For the MiG, it is 0 deg.
  • CHSTAT - the % of the mac at which the sweep angle will be referenced. Usually this is c/4or 0.25.
  • DHDAHI - the dihedral of the inboard panel. If the inboard and outboard panel dihedral isthe same (constant dihedral across the wing), then only DHDADI is inputted. For the MiG,the wing dihedral is -3 deg.
  • TYPE - different planform types (refer to manual). Will be set to 1.

These values are inputted into the for005 file as follows:

$WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,
CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,
TWISTA=0.0,DHDADI=-3.0,TYPE=1.0$

 

 

THE HTPLNF NAMELIST

 

The horizontal tail is described the same way as wing using the same variables. Because the geometry of the HT is simpler, we will only use the following variables: CHRDTP, SSPNE, SSPN, CHRDR, SAVSI, CHSTAT, and TYPE.

  • CHRDTP is 1.86 feet
  • SSPNE is 5.42 feet
  • SSPN is 5.43 feet
  • CHRDR is 4.69 feet
  • SAVSI is 45 degrees
  • CHSTAT is 0.25
  • TYPE is 1

And so the values are inputted into the HTPLNF namelist as follows:

$HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,
CHSTAT=0.25,TYPE=1.0$

 

THE VTPLNF NAMELIST

 

The vertical tail is described the same way as wing using the same variables. Because the geometry of the VT is simpler, we will only use the following variables: CHRDTP, SSPNE, SSPN, CHRDR, SAVSI, CHSTAT, and TYPE.

  • CHRDTP is 3.76 feet
  • SSPNE is 6.05 feet
  • SSPN is 8.18 feet
  • CHRDR is 12.47 feet
  • SAVSI is 55 degrees (not measured)
  • CHSTAT is 0.25
  • TYPE is 1

And so the values are inputted into the VTPLNF namelist as follows:

$VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,
CHSTAT=0.25,TYPE=1.0$

 

 

AIRFOIL DESIGNATIONS

 

We cannot forget to input the airfoil shapes for the wing and tails. Page 74 and 75 of volume I has some information on this. If the wing was a NACA-2412, we would input into the for005 file: NACAW-4-2412. The "NACA" indicates that it is a NACA airfoil, for which DATCOM has built in data. "W" indicates that the airfoil is to be applied to the wing ("H" for HT, and "V" for VT). "4" indicates that it is a 4 series airfoil (DATCOM accepts 1, 4, 5, and 6 series airfoils). And after that is the airfoil designation number, in this example it is "2412."

 

For the MiG, the NACA 66-012 airfoil we be used for the wing, and the 66-009 for the tails. They will simply be inputted into DATCOM as follows:

NACA-W-6-66-012 
NACA-H-6-66-009 
NACA-V-6-66-009

 

 

TERMINATING THE FILE

 

There are a number of commands that can be placed at the end of the file to specify information and give more data. We will use 3 commands:

  • DIM FT - specifies that all of the dimension were given in feet and all out the output shouldbe in "English" units
  • BUILD - show the data for all of the components. not just the aircraft
  • PLOT - generate a plot file (for013.dat) to input into a plotting program

Finally, the file ends with "NEXT CASE". In the input file this looks like:

DIM FT
BUILD
PLOT
NEXT CASE

 

 

THE FULL for005.dat FILE

 

Here is the full input file that will be run by DATCOM.

CASEID ----- MIKOYAN-GUREVICH MiG-17 -----
 $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,
  0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,
  WT=13395.0,LOOP=1.$
 $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,
  ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$
 $OPTINS SREF=243.0$
 $BODY NX=8.0,
  X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,
  S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$
NACA-W-6-66-012
 $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,
  CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,
  TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$
NACA-H-6-66-009
 $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,
  CHSTAT=0.25,TYPE=1.0$
NACA-V-6-66-009
 $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,
  CHSTAT=0.25,TYPE=1.0$
DIM FT
BUILD
PLOT
NEXT CASE

 

 

OUTPUT File

 

  ****************************************************
  *    USAF STABILITY AND CONTROL  DIGITAL DATCOM    *
  *    PROGRAM REV. JAN 96   DIRECT INQUIRIES TO:    *
  *    WRIGHT LABORATORY  (WL/FIGC)  ATTN: W. BLAKE  *
  *      WRIGHT PATTERSON AFB, OHIO  45433           *
  *    PHONE (513) 255-6764,   FAX (513) 258-4054    *
  ****************************************************
1                         CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0******************************  INPUT DATA CARDS  ******************************

 CASEID ----- MIKOYAN-GUREVICH MiG-17 -----                                      
  $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,                 
   0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,                    
   WT=13395.0,LOOP=1.$                                                           
  $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,                   
   ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$                                              
  $OPTINS SREF=243.0$                                                            
  $BODY NX=8.0,                                                                  
   X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,                             
   S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$                              
 NACA-W-6-66-012                                                                 
  $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,                       
   CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,                      
   TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$                                  
 NACA-H-6-66-009                                                                 
  $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,                
   CHSTAT=0.25,TYPE=1.0$                                                         
 NACA-V-6-66-009                                                                 
  $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,               
   CHSTAT=0.25,TYPE=1.0$                                                         
 DIM FT                                                                          
 BUILD                                                                           
 PLOT                                                                            
 NEXT CASE                                                                       
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
 CASEID ----- MIKOYAN-GUREVICH MiG-17 -----                                      
  $FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,ALSCHD(1)=-4.0,-2.0,                 
   0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,NALT=1.0,ALT(1)=5000.0,                    
   WT=13395.0,LOOP=1.$                                                           
  $SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,XH=28.73,                   
   ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$                                              
  $OPTINS SREF=243.0$                                                            
  $BODY NX=8.0,                                                                  
   X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,                             
   S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$                              
 NACA-W-6-66-012                                                                 
  $WGPLNF CHRDTP=7.02,SSPNOP=11.32,SSPNE=13.41,SSPN=15.71,                       
   CHRDBP=8.4,CHRDR=14.0,SAVSI=45.0,SAVSO=45.0,CHSTAT=0.25,                      
   TWISTA=0.0,DHDADI=-3.0,DHDADO=-3.0,TYPE=1.0$                                  
 NACA-H-6-66-009                                                                 
  $HTPLNF CHRDTP=1.86,SSPNE=5.42,SSPN=5.43,CHRDR=4.69,SAVSI=45.0,                
   CHSTAT=0.25,TYPE=1.0$                                                         
 NACA-V-6-66-009                                                                 
  $VTPLNF CHRDTP=3.76,SSPNE=6.05,SSPN=8.18,CHRDR=12.47,SAVSI=55.0,               
   CHSTAT=0.25,TYPE=1.0$                                                         
 DIM FT                                                                          
 BUILD                                                                           
 PLOT                                                                            
 NEXT CASE                                                                       
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                        WING SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09699 /DEG.

                                    LEADING EDGE RADIUS =   0.00993 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.12000 FRACTION CHORD

                                                DELTA-Y =   2.01961 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.11881 /DEG.      XAC =   0.26851
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                   HORIZONTAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09870 /DEG.

                                    LEADING EDGE RADIUS =   0.00559 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.09000 FRACTION CHORD

                                                DELTA-Y =   1.52747 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.12143 /DEG.      XAC =   0.26444
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                    VERTICAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =   0.00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =  -0.00000 DEG.

                                 IDEAL LIFT COEFFICIENT =   0.00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   0.00000

                             MACH ZERO LIFT-CURVE-SLOPE =   0.09870 /DEG.

                                    LEADING EDGE RADIUS =   0.00559 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =   0.09000 FRACTION CHORD

                                                DELTA-Y =   1.52747 PERCENT CHORD


0                         MACH= 0.6000 LIFT-CURVE-SLOPE =   0.12143 /DEG.      XAC =   0.26444
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                   DATCOM BODY ALONE CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.006   -0.003   -0.0151  -0.004    0.005    3.976    8.326E-04    3.835E-03   -8.326E-04   -1.106E-03    0.000E+00
   -2.0    0.005   -0.002   -0.0076  -0.002    0.005    4.063    8.580E-04    3.784E-03   -8.580E-04   -1.092E-03    0.000E+00
    0.0    0.005    0.000    0.0000   0.000    0.005   ******    8.453E-04    3.810E-03   -8.453E-04   -1.099E-03    0.000E+00
    2.0    0.005    0.002    0.0076   0.002    0.005    4.063    8.580E-04    3.784E-03   -8.580E-04   -1.092E-03    0.000E+00
    4.0    0.006    0.003    0.0151   0.004    0.005    3.976    8.832E-04    3.734E-03   -8.832E-04   -1.077E-03    0.000E+00
    6.0    0.006    0.005    0.0226   0.006    0.005    3.887    9.082E-04    3.685E-03   -9.082E-04   -1.063E-03    0.000E+00
    8.0    0.006    0.007    0.0299   0.008    0.005    3.798    9.328E-04    3.636E-03   -9.328E-04   -1.049E-03    0.000E+00
   10.0    0.007    0.009    0.0371   0.010    0.005    3.709    9.569E-04    3.588E-03   -9.569E-04   -1.035E-03    0.000E+00
   12.0    0.008    0.011    0.0442   0.012    0.005    3.619    9.804E-04    3.541E-03   -9.804E-04   -1.022E-03    0.000E+00
   14.0    0.008    0.013    0.0513   0.015    0.005    3.530    1.004E-03    3.495E-03   -1.004E-03   -1.008E-03    0.000E+00
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                      WING ALONE CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.008   -0.141    0.0886  -0.141   -0.002   -0.629    4.578E-02   -2.828E-02   -2.768E-04    2.377E-05    1.160E-03
   -2.0    0.006   -0.046    0.0292  -0.046    0.004   -0.629    4.671E-02   -2.912E-02   -2.948E-04    2.562E-06    7.170E-04
    0.0    0.006    0.046   -0.0279   0.046    0.006   -0.603    4.671E-02   -2.853E-02   -2.948E-04    2.561E-06    2.837E-04
    2.0    0.008    0.141   -0.0849   0.141    0.003   -0.603    4.777E-02   -3.006E-02   -2.768E-04    2.375E-05   -1.595E-04
    4.0    0.013    0.237   -0.1481   0.238   -0.004   -0.623    4.861E-02   -3.303E-02   -2.378E-04    6.761E-05   -6.127E-04
    6.0    0.021    0.335   -0.2170   0.335   -0.015   -0.647    4.904E-02   -3.303E-02   -1.776E-04    1.350E-04   -1.072E-03
    8.0    0.031    0.433   -0.2802   0.433   -0.030   -0.646    4.798E-02   -2.921E-02   -9.633E-05    2.257E-04   -1.533E-03
   10.0    0.043    0.527   -0.3339   0.527   -0.049   -0.634    4.396E-02   -2.311E-02    3.331E-06    3.337E-04   -1.972E-03
   12.0    0.056    0.609   -0.3726   0.608   -0.072   -0.613    3.844E-02   -1.962E-02    1.083E-04    4.457E-04   -2.358E-03
   14.0    0.068    0.681   -0.4124   0.677   -0.098   -0.609    3.314E-02   -2.011E-02    2.138E-04    5.565E-04   -2.694E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                    HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.002   -0.032    0.0757  -0.032   -0.000   -2.349    8.325E-03   -1.965E-02    1.322E-06    2.767E-06    5.983E-05
   -2.0    0.001   -0.016    0.0371  -0.016    0.001   -2.343    8.044E-03   -1.892E-02    3.215E-07    6.678E-07    2.940E-05
    0.0    0.001    0.000    0.0000   0.000    0.001   ******    7.904E-03   -1.854E-02    0.000E+00    0.000E+00   -1.218E-36
    2.0    0.001    0.016   -0.0370   0.016    0.001   -2.339    8.044E-03   -1.887E-02    3.215E-07    6.677E-07   -2.940E-05
    4.0    0.002    0.032   -0.0755   0.032   -0.000   -2.343    8.289E-03   -1.953E-02    1.322E-06    2.767E-06   -5.983E-05
    6.0    0.003    0.049   -0.1152   0.049   -0.002   -2.351    8.461E-03   -2.009E-02    3.039E-06    6.409E-06   -9.105E-05
    8.0    0.004    0.066   -0.1559   0.066   -0.005   -2.363    8.558E-03   -2.057E-02    5.487E-06    1.166E-05   -1.228E-04
   10.0    0.006    0.083   -0.1974   0.083   -0.008   -2.378    8.377E-03   -2.050E-02    8.653E-06    1.852E-05   -1.547E-04
   12.0    0.008    0.100   -0.2378   0.099   -0.012   -2.400    7.411E-03   -1.865E-02    1.240E-05    2.652E-05   -1.851E-04
   14.0    0.011    0.113   -0.2720   0.112   -0.017   -2.428    5.900E-03   -1.551E-02    1.604E-05    3.411E-05   -2.098E-04
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                     VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.001    0.000    0.0000   0.000    NDM     ******    0.000E+00    0.000E+00   -7.955E-03    3.809E-03   -1.114E-03
   -2.0                                                                                                             -9.827E-04
    0.0                                                                                                             -8.503E-04
    2.0                                                                                                             -7.168E-04
    4.0                                                                                                             -5.825E-04
    6.0                                                                                                             -4.475E-04
    8.0                                                                                                             -3.119E-04
   10.0                                                                                                             -1.760E-04
   12.0                                                                                                             -3.980E-05
   14.0                                                                                                              9.641E-05
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                       WING-BODY CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.014   -0.199    0.0910  -0.199   -0.000   -0.456    6.394E-02   -3.075E-02   -1.194E-03   -1.190E-03    1.351E-03
   -2.0    0.011   -0.072    0.0307  -0.073    0.009   -0.422    6.263E-02   -2.953E-02                              7.584E-04
    0.0    0.011    0.052   -0.0272   0.052    0.011   -0.527    6.257E-02   -2.894E-02                              1.777E-04
    2.0    0.013    0.178   -0.0851   0.178    0.007   -0.477    6.387E-02   -3.071E-02                             -4.141E-04
    4.0    0.019    0.307   -0.1500   0.308   -0.003   -0.488    6.503E-02   -3.415E-02                             -1.019E-03
    6.0    0.027    0.438   -0.2217   0.438   -0.019   -0.506    6.566E-02   -3.434E-02                             -1.633E-03
    8.0    0.037    0.570   -0.2874   0.569   -0.042   -0.505    6.444E-02   -3.026E-02                             -2.250E-03
   10.0    0.050    0.696   -0.3427   0.694   -0.072   -0.494    5.945E-02   -2.354E-02                             -2.840E-03
   12.0    0.063    0.807   -0.3816   0.803   -0.106   -0.475    5.233E-02   -1.966E-02                             -3.364E-03
   14.0    0.077    0.905   -0.4214   0.897   -0.144   -0.470    4.531E-02   -2.017E-02                             -3.821E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                 BODY-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.007   -0.036    0.0605  -0.036    0.005   -1.674    9.241E-03   -1.556E-02   -3.717E-01   -1.190E-03    4.503E-05
   -2.0    0.007   -0.018    0.0300  -0.018    0.006   -1.686    8.934E-03   -1.499E-02                              2.038E-05
    0.0    0.006    0.000    0.0006   0.000    0.006   ******    8.780E-03   -1.480E-02                             -3.429E-06
    2.0    0.007    0.018   -0.0292   0.018    0.006   -1.643    8.934E-03   -1.537E-02                             -2.724E-05
    4.0    0.007    0.036   -0.0609   0.036    0.005   -1.684    9.205E-03   -1.629E-02                             -5.189E-05
    6.0    0.009    0.054   -0.0944   0.055    0.003   -1.716    9.402E-03   -1.713E-02                             -7.717E-05
    8.0    0.011    0.073   -0.1294   0.074    0.000   -1.747    9.524E-03   -1.787E-02                             -1.029E-04
   10.0    0.013    0.092   -0.1659   0.093   -0.003   -1.777    9.363E-03   -1.806E-02                             -1.288E-04
   12.0    0.016    0.111   -0.2017   0.112   -0.007   -1.805    8.414E-03   -1.642E-02                             -1.537E-04
   14.0    0.019    0.126   -0.2315   0.127   -0.012   -1.823    6.920E-03   -1.346E-02                             -1.745E-04
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                  BODY-VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.006   -0.003   -0.0151  -0.004    0.006    3.908    8.326E-04    3.835E-03   -8.788E-03    2.702E-03   -1.114E-03
   -2.0    0.006   -0.002   -0.0076  -0.002    0.006    3.992    8.580E-04    3.784E-03                             -9.827E-04
    0.0    0.006    0.000    0.0000   0.000    0.006   ******    8.453E-04    3.810E-03                             -8.503E-04
    2.0    0.006    0.002    0.0076   0.002    0.006    3.992    8.580E-04    3.784E-03                             -7.168E-04
    4.0    0.006    0.003    0.0151   0.004    0.006    3.908    8.832E-04    3.734E-03                             -5.825E-04
    6.0    0.007    0.005    0.0226   0.006    0.006    3.822    9.082E-04    3.685E-03                             -4.475E-04
    8.0    0.007    0.007    0.0299   0.008    0.006    3.736    9.328E-04    3.636E-03                             -3.119E-04
   10.0    0.008    0.009    0.0371   0.010    0.006    3.649    9.569E-04    3.588E-03                             -1.760E-04
   12.0    0.008    0.011    0.0442   0.012    0.006    3.562    9.804E-04    3.541E-03                             -3.980E-05
   14.0    0.009    0.013    0.0513   0.015    0.006    3.475    1.004E-03    3.495E-03                              9.641E-05
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                               WING-BODY-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.015   -0.219    0.1391  -0.220    0.000   -0.633    6.830E-02   -4.069E-02   -1.192E-03   -1.187E-03    1.411E-03
   -2.0    0.012   -0.084    0.0592  -0.085    0.009   -0.699    6.671E-02   -3.906E-02                              7.878E-04
    0.0    0.012    0.048   -0.0171   0.048    0.012   -0.360    6.638E-02   -3.789E-02                              1.777E-04
    2.0    0.015    0.181   -0.0924   0.182    0.008   -0.509    6.740E-02   -3.907E-02                             -4.435E-04
    4.0    0.020    0.317   -0.1734   0.318   -0.002   -0.546    6.830E-02   -4.193E-02                             -1.079E-03
    6.0    0.029    0.454   -0.2601   0.455   -0.019   -0.572    6.873E-02   -4.172E-02                             -1.724E-03
    8.0    0.041    0.592   -0.3403   0.592   -0.042   -0.575    6.744E-02   -3.754E-02                             -2.372E-03
   10.0    0.055    0.724   -0.4102   0.723   -0.072   -0.568    6.239E-02   -3.078E-02                             -2.995E-03
   12.0    0.070    0.842   -0.4634   0.838   -0.106   -0.553    5.526E-02   -2.697E-02                             -3.549E-03
   14.0    0.086    0.945   -0.5181   0.938   -0.146   -0.552    4.829E-02   -2.773E-02                             -4.031E-03
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -4.0      1.000     -1.454        0.479
                                     -2.0      1.000     -0.496        0.491
                                      0.0      1.000      0.510        0.520
                                      2.0      1.000      1.582        0.554
                                      4.0      1.000      2.726        0.589
                                      6.0      1.000      3.938        0.620
                                      8.0      1.000      5.207        0.634
                                     10.0      1.000      6.473        0.615
                                     12.0      1.000      7.669        0.590
                                     14.0      1.000      8.835        0.583
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                                WING-BODY-VERTICAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.015   -0.199    0.0910  -0.199    0.001   -0.456    6.394E-02   -3.075E-02   -9.149E-03    2.619E-03    2.375E-04
   -2.0    0.012   -0.072    0.0307  -0.073    0.009   -0.422    6.263E-02   -2.953E-02                             -2.243E-04
    0.0    0.012    0.052   -0.0272   0.052    0.012   -0.527    6.257E-02   -2.894E-02                             -6.726E-04
    2.0    0.014    0.178   -0.0851   0.178    0.008   -0.477    6.387E-02   -3.071E-02                             -1.131E-03
    4.0    0.020    0.307   -0.1500   0.308   -0.002   -0.488    6.503E-02   -3.415E-02                             -1.602E-03
    6.0    0.027    0.438   -0.2217   0.439   -0.018   -0.506    6.566E-02   -3.434E-02                             -2.080E-03
    8.0    0.038    0.570   -0.2874   0.569   -0.041   -0.505    6.444E-02   -3.026E-02                             -2.562E-03
   10.0    0.051    0.696   -0.3427   0.694   -0.071   -0.494    5.945E-02   -2.354E-02                             -3.016E-03
   12.0    0.064    0.807   -0.3816   0.803   -0.105   -0.475    5.233E-02   -1.966E-02                             -3.404E-03
   14.0    0.078    0.905   -0.4214   0.897   -0.143   -0.470    4.531E-02   -2.017E-02                             -3.725E-03
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                ----- MIKOYAN-GUREVICH MiG-17 -----
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0 0.600    5000.00     658.18   1.7609E+03     500.843     3.6904E+06           243.000      9.065    31.420    11.170     0.000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
   -4.0    0.016   -0.219    0.1391  -0.220    0.001   -0.633    6.830E-02   -4.069E-02   -9.147E-03    2.622E-03    2.974E-04
   -2.0    0.013   -0.084    0.0592  -0.085    0.010   -0.699    6.671E-02   -3.906E-02                             -1.949E-04
    0.0    0.013    0.048   -0.0171   0.048    0.013   -0.360    6.638E-02   -3.789E-02                             -6.726E-04
    2.0    0.016    0.181   -0.0924   0.182    0.009   -0.509    6.740E-02   -3.907E-02                             -1.160E-03
    4.0    0.021    0.317   -0.1734   0.318   -0.001   -0.546    6.830E-02   -4.193E-02                             -1.662E-03
    6.0    0.030    0.454   -0.2601   0.455   -0.018   -0.572    6.873E-02   -4.172E-02                             -2.171E-03
    8.0    0.042    0.592   -0.3403   0.592   -0.041   -0.575    6.744E-02   -3.754E-02                             -2.684E-03
   10.0    0.056    0.724   -0.4102   0.723   -0.071   -0.568    6.239E-02   -3.078E-02                             -3.171E-03
   12.0    0.071    0.842   -0.4634   0.838   -0.106   -0.553    5.526E-02   -2.697E-02                             -3.589E-03
   14.0    0.087    0.945   -0.5181   0.938   -0.145   -0.552    4.829E-02   -2.773E-02                             -3.935E-03
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                     -4.0      1.000     -1.454        0.479
                                     -2.0      1.000     -0.496        0.491
                                      0.0      1.000      0.510        0.520
                                      2.0      1.000      1.582        0.554
                                      4.0      1.000      2.726        0.589
                                      6.0      1.000      3.938        0.620
                                      8.0      1.000      5.207        0.634
                                     10.0      1.000      6.473        0.615
                                     12.0      1.000      7.669        0.590
                                     14.0      1.000      8.835        0.583
0*** VEHICLE WEIGHT =  13395.00 LB.
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.12422
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.

 

 

for013 File

 

  1.0000E+00  1.0000E+01  6.0000E-01  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  2.4300E+02  9.0649E+00  1.6000E-04  3.1420E+01
  T  T  T  T  T  T  T  T  T  T  T  F  F  F  F  F  T  F  F  F  F  F  F  F  F  F  T  F  F  F  F  F  F  T
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  0.0000E+00 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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  0.0000E+00 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
 -7.9550E-03 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30
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  3.8088E-03 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30 -1.0000E-30
  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30  1.0000E-30
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REFERENCES

 

Data and History

Blueprints of Mig-17, http://www.the-blueprints.com

History, http://www.globalsecurity.org/military/world/russia/mig-17.htm

History & Data, http://www.vectorsite.net/avmig15_2.html

Pictures, http://www.suchoj.com/galerie/index.htm?http://www.suchoj.com/andere/MiG-17/galerie.shtml

 

 

 

 

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미국 공군의 DIGITAL DATCOM은 고정익 항공기의 정적 안정성, 제어 및 동적 특성을 계산하려고 개발한 컴퓨터 프로그램이다. DIGITAL DATCOM을 구동하려면 항공기의 형태를 정의하는 입력 파일이 필요하며, 지정된 비행 조건에 따라 해당 무차원 안정성 도함수를 출력한다. 계산 결과는 비행 역학에서 필요한 물리량을을 계산하는 데 사용할 수 있다.

 

이 프로그램에는 초음속 마하 수에서 항공기 균형을 위한 제어 편향 및 공기역학적 증분을 계산하는 조정 옵션이 포함되어 있다. 사용자 매뉴얼에는 프로그램 기능, 입력 및 출력 특성, 예제 문제가 설명되어 있다. 프로그램의 사용자 친화적 기능에는 입력 요구사항 최소화, 입력 오류 분석, 응용 유연성을 위한 다양한 옵션이 포함되었다. [AFFDL-TR-79-3032에서 발췌]

 

1976년 2월, USAF Stability and Control DATCOM에 포함된 방법, 특히 4, 5, 6 및 7에 포함된 방법을 자동화하는 작업이 시작되었다. 이 작업은 미국 공군과 계약을 맺고 McDonnell Douglas Corporation이 Wright-Patterson 공군 기지에 있는 공군 비행 역학 연구소의 엔지니어와 함께 수행했다. DIGITAL DATCOM의 구현은 1978년 11월에 완료되었다. 이 프로그램은 FORTRAN IV로 작성되었으며 이후 업데이트되었다. 그러나 프로그램의 핵심은 일정하게 유지되었다.

 

Digital DATCOM의 사용 방법을 설명하는 보고서가 세 권으로 나누어서 발행되었다. 보고서는 다음과 같다.

  • Volume I, 사용 설명서
  • Volume II, DATCOM의 구현
  • Volume III, Plot Module

다음 사이트에서 DIGITAL DATCOM의 FORTRAN 소스를 다운로드할 수 있다.

USAF Digital Datcom

 

USAF Digital Datcom

PDAS home > Contents > Datcom Public Domain Aeronautical Software (PDAS)   Digital Datcom This computer program calculates static stability, high lift and control, and dynamic derivative characteristics using the methods contained in the USAF Stability an

www.pdas.com

 

하지만 이 소스는 FORTRAN IV로 작성되었으므로 오래된 포트란 문법이 많이 적용되었다. 따라서 컴파일할 때 다음 명령어를 사용해야 한다.

gfortran  -std=legacy datcom.f -o datcom.exe

 

수정 사항

 

1. 사용자가 입력한 입력 파일의 이름과 같은 이름으로 출력 파일을 만든다.

2. for013.dat는 사용자가 정의한 이름.013으로 수정

3. for014.dat는 사용자가 정의한 이름.014로 수정

 

datcom.exe
1.51MB

 

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