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DIGITAL DATCOM은 그래픽 인터페이스 없이 텍스트 기반 입력 파일만으로 항공기의 공기역학적 특성을 계산하는 프로그램이다. 처음 접하는 사용자에게는 다소 낯설게 느껴질 수 있으나, 입력 구조와 명령어 체계를 이해하면 비교적 체계적으로 모델을 구축할 수 있다. 이 튜토리얼에서는 단순하고 명확한 기하 형상을 가진 미코얀-구레비치 MiG-17 전투기를 예제 항공기로 선택하여 DATCOM 모델 구축 전 과정을 설명한다.
MiG-17 선택 이유와 기본 특성
MiG-17은 1949년 소련의 미코얀-구레비치 설계국이 MiG-15의 후속으로 개발한 전투기로, 마하 1에 근접한 속도에서도 우수한 기동성을 발휘했다. DATCOM 튜토리얼용으로 이 항공기를 선택한 이유는 기하 형상의 단순성 때문이다. 기체 단면이 거의 원형에 가까우며, 날개와 꼬리 형상도 복잡하지 않아 입력 매개변수를 최소화할 수 있다. 날개폭은 약 31피트 7인치, 전장은 36피트 5인치이며, 날개 후퇴각은 약 45도, 이면각은 -3도, 경사각은 1도이다.
한 가지 중요한 가정이 있다. MiG-17은 러시아제 TsAGI S-12(12%) 에어포일을 사용하는데, DATCOM은 러시아 에어포일 데이터를 내장하고 있지 않다. 이 튜토리얼에서는 TsAGI S-12(12%)를 NACA 66-012와 동일하다고 가정하였다. 이는 검증된 가정이 아니므로 결과 해석 시 유의해야 한다.
입력 파일 구조
DATCOM 입력 파일(for005)은 매우 엄격한 형식을 따른다. 형식 오류가 있으면 분석이 실행되지 않는다. 파일은 CASEID로 시작하며, 이후 모든 데이터는 $로 시작하고 $로 종료되는 namelist 블록으로 구성된다.
이 예제에서 사용하는 주요 namelist는 다음과 같다. $FLTCON은 마하수, 고도, 받음각 등 비행 조건을 정의하고, $SYNTHS는 무게중심 및 날개·꼬리 표면의 위치를 설정한다. $BODY는 기체 단면 형상을 스테이션별로 정의하며, $WGPLNF, $HTPLNF, $VTPLNF는 각각 주익, 수평 꼬리, 수직 꼬리의 평면 형상을 입력한다.
주요 명령어별 입력 내용
FLTCON — 비행 조건 정의
마하수 0.6, 고도 5,000피트 조건에서 받음각 -4도부터 14도까지 총 10개 포인트로 해석을 수행한다. 항공기 중량은 13,395파운드로 입력한다.
$FLTCON NMACH=1.0,MACH(1)=0.6,NALPHA=10.0,
ALSCHD(1)=-4.0,-2.0,0.0,2.0,4.0,6.0,8.0,10.0,12.0,14.0,
NALT=1.0,ALT(1)=5000.0,WT=13395.0,LOOP=1.$
SYNTHS — 기준선 대비 각 구성요소 위치
모든 수평 측정은 기수(nose)에서, 수직 측정은 기체 중심의 기준선에서 측정한다. 무게중심 위치 정보가 주어지지 않았으므로 XCG는 11.17피트로 임의 설정하였다.
$SYNTHS XCG=11.17,ZCG=0.0,XW=3.63,ZW=0.42,ALIW=1.0,
XH=28.73,ZH=5.24,ALIH=0.0,XV=18.3,ZV=0.0$
BODY — 기체 형상 정의
기체를 코 끝부터 후미까지 8개 스테이션으로 나누어 각 위치의 단면적을 입력한다. MiG-17의 기체 단면은 원형으로 가정하였으며, 최대 단면적은 스테이션 3과 4에서 약 16.89 제곱피트이다.
$BODY NX=8.0,
X(1)=0.0,0.74,8.35,13.14,19.35,24.41,28.41,30.77,
S(1)=5.19,9.32,16.89,16.89,15.94,11.12,5.85,2.5$
날개 및 꼬리 형상 정의
주익(WGPLNF)은 내측 패널과 외측 패널로 구성되며, 루트 코드 14.0피트, 팁 코드 7.02피트, 후퇴각 45도로 입력한다. 수평 꼬리(HTPLNF)는 루트 코드 4.69피트, 팁 코드 1.86피트, 마찬가지로 후퇴각 45도이다. 수직 꼬리(VTPLNF)는 루트 코드 12.47피트, 팁 코드 3.76피트, 후퇴각 55도로 설정하였다. 에어포일은 날개에 NACA 66-012, 수평·수직 꼬리에 NACA 66-009를 적용한다.
파일 말미에는 DIM FT(피트 단위 지정), BUILD(전체 구성 출력), PLOT(플롯 파일 생성), NEXT CASE(케이스 종료)를 추가한다.
출력 결과 해석
프로그램 실행 후 출력 파일(for006)에는 기체 단독, 날개 단독, 수평 꼬리, 수직 꼬리, 동체-날개, 동체-꼬리, 그리고 **전체 형상(Wing-Body-HT-VT)**에 이르기까지 구성 요소 조합별로 안정성 도함수가 출력된다.
최종 전체 형상 해석 결과에서 마하 0.6, 받음각 0도 기준 주요 값은 다음과 같다. 양력계수 $C_L = 0.048$, 항력계수 $C_D = 0.013$, 피칭 모멘트 계수 $C_M = -0.017$이다. 양력 곡선 기울기 $C_{L\alpha} = 0.0664$/deg, 피칭 모멘트 기울기 $C_{M\alpha} = -0.0379$/deg로 산출되었다. $C_{M\alpha}$가 음수인 것은 항공기가 정적으로 종방향 안정을 갖는다는 의미이다. 수평 꼬리의 세류각(downwash) 데이터도 함께 출력되어, 받음각이 증가할수록 세류각도 증가하는 경향을 확인할 수 있다.
유의사항 및 한계
이 모델은 몇 가지 가정을 포함하고 있어 결과의 절대적 정확도에는 한계가 있다. 무게중심 위치를 임의로 설정하였고, TsAGI 에어포일을 NACA 에어포일로 대체하였으며, 캐노피 형상을 생략하였다. 또한 수직 꼬리 후퇴각(55도)도 추정값이다. 그러나 DATCOM 모델 구축 절차와 입력 파일 형식을 익히는 학습 목적으로는 충분히 유효하며, 설계 초기 단계의 경향성 파악에도 활용할 수 있다.
도면 및 치수
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
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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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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