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이 세상의 거의 모든 화학종의 혼합물에서 화학 평형을 계산하는 컴퓨터 코드의 근본은 NASA에서 개발한 CEA이다. 그만큼 대단한 코드라고 할 수 있다. 현재는 다운로드가 사라졌지만 JAVA로 개발한 GUI가 있었다. 이 GUI는 우선 JAVA 런타임이 필요하고, 화학종 데이터가 데이터베이스로 구성되어 있지 않다. 그래서 때로는 화학 평형을 계산하는 사람마다 화학 특성을 다르게 입력하여 계산 결과가 다를 수도 있으므로 회사를 비롯한 어떤 공통된 프로세스가 필요한 곳에서 사용할 때 약간의 문제가 발생할 수 있다.
화학종의 데이터베이스가 존재하는 상용 프로그램이 있다. Explo5라는 소프트웨어이다. 하지만 상용 프로그램이므로 비용을 지불해야만 한다.
그런데 화학종 데이터베이스도 있고, 무료 소프트웨어가 있다. 바로 RPA 소프트웨어이다.
RP Software+Engineering UG | RPA-C | Features
RP Software+Engineering UG | RPA-C | Features
RPA-C Features RPA-C is a combustion analysis tool used in the automotive industry to design airbag inflators and micro gas generators. It can also be used as a general-purpose code for combustion analysis of propellants and pyrotechnics mixtures. The soft
www.rocket-propulsion.com
RPA는 자동차 산업에서 에어백 인플레이터와 마이크로 가스 발생기를 설계하는 데 사용되는 연소 분석 도구입니다. 또한 추진제와 폭약 혼합물의 연소 분석을 위한 범용 코드로도 사용할 수 있습니다.
소프트웨어는 다음을 수행할 수 있습니다:
- 응축 생성물을 생성하는 조성물을 포함한 다양한 초기 혼합물의 연소 문제 해결
- 정확한 방법과 불활성 희석제(Ar) 방법을 사용한 폭발열(HEX) 추정
- 견고하고 입증되었으며 업계에서 인정한 깁스 자유 에너지 최소화 접근법을 사용하여 반응 혼합물의 열역학적 특성 계산
- 반응 성분 및 생성물에 대한 확장 가능한 데이터베이스
- NASA CEA 및 PROPEP 형식에서 화학종 입수
- 화학종을 수정하거나 사용자 지정 성분을 추가하는 화학종 편집기
- 타사 도구 및 사용자 지정 스크립트(예: Matlab, Scilab 또는 Octave)에서 RPA 기능에 접근할 수 있는 스크립팅 유틸리티
- 맞춤형 솔루션 개발을 위한 Scilab 네이티브 플러그인
다음은 NASA CEA와 RPA를 사용한 예이다.
Example
Oxidizer: O2(L)
Fuel: CH4(L)
Pc=1000psi
O/F=4.0 (near stoichiometric)
Ac/At=3.0
Ae/At=10.0, 25.0, 50.0
NASA CEA
NASA CEA 결과
problem o/f=4.0,
rocket equilibrium frozen nfz=1 tcest,k=3800
p,psia=1000.0,
sub,ae/at=3.0,
sup,ae/at=10.0,25.0,50.0,
react
fuel=CH4(L)
oxid=O2(L)
output transport
plot aeat t p ivac isp mach cf
end
*******************************************************************************
NASA-GLENN CHEMICAL EQUILIBRIUM PROGRAM CEA2, MAY 21, 2004
BY BONNIE MCBRIDE AND SANFORD GORDON
REFS: NASA RP-1311, PART I, 1994 AND NASA RP-1311, PART II, 1996
*******************************************************************************
problem o/f=4.0,
rocket equilibrium frozen nfz=1 tcest,k=3800
p,psia=1000.0,
sub,ae/at=3.0,
sup,ae/at=10.0,25.0,50.0,
react
fuel=CH4(L)
oxid=O2(L)
output transport
plot aeat t p ivac isp mach cf
end
OPTIONS: TP=F HP=F SP=F TV=F UV=F SV=F DETN=F SHOCK=F REFL=F INCD=F
RKT=T FROZ=T EQL=T IONS=F SIUNIT=T DEBUGF=F SHKDBG=F DETDBG=F TRNSPT=T
TRACE= 0.00E+00 S/R= 0.000000E+00 H/R= 0.000000E+00 U/R= 0.000000E+00
Pc,BAR = 68.947304
Pc/P =
SUBSONIC AREA RATIOS = 3.0000
SUPERSONIC AREA RATIOS = 10.0000 25.0000 50.0000
NFZ= 1 Mdot/Ac= 0.000000E+00 Ac/At= 0.000000E+00
WARNING!! AMOUNT MISSING FOR REACTANT 1.
PROGRAM SETS WEIGHT PERCENT = 100. (REACT)
WARNING!! AMOUNT MISSING FOR REACTANT 2.
PROGRAM SETS WEIGHT PERCENT = 100. (REACT)
REACTANT WT.FRAC (ENERGY/R),K TEMP,K DENSITY
EXPLODED FORMULA
F: CH4(L) 1.000000 -0.107322E+05 111.64 0.0000
C 1.00000 H 4.00000
O: O2(L) 1.000000 -0.156101E+04 90.17 0.0000
O 2.00000
SPECIES BEING CONSIDERED IN THIS SYSTEM
(CONDENSED PHASE MAY HAVE NAME LISTED SEVERAL TIMES)
LAST thermo.inp UPDATE: 9/09/04
g 7/97 *C tpis79 *CH g 4/02 CH2
g 4/02 CH3 g11/00 CH2OH g 7/00 CH3O
g 8/99 CH4 g 7/00 CH3OH srd 01 CH3OOH
tpis79 *CO g 9/99 *CO2 tpis91 COOH
tpis91 *C2 g 6/01 C2H g 1/91 C2H2,acetylene
g 5/01 C2H2,vinylidene g 4/02 CH2CO,ketene g 3/02 O(CH)2O
srd 01 HO(CO)2OH g 7/01 C2H3,vinyl g 6/96 CH3CO,acetyl
g 1/00 C2H4 g 8/88 C2H4O,ethylen-o g 8/88 CH3CHO,ethanal
g 6/00 CH3COOH srd 01 OHCH2COOH g 7/00 C2H5
g 7/00 C2H6 g 8/88 C2H5OH g 7/00 CH3OCH3
srd 01 CH3O2CH3 g 8/00 C2O tpis79 *C3
n 4/98 C3H3,1-propynl n 4/98 C3H3,2-propynl g 2/00 C3H4,allene
g 1/00 C3H4,propyne g 5/90 C3H4,cyclo- g 3/01 C3H5,allyl
g 2/00 C3H6,propylene g 1/00 C3H6,cyclo- g 6/01 C3H6O,propylox
g 6/97 C3H6O,acetone g 1/02 C3H6O,propanal g 7/01 C3H7,n-propyl
g 9/85 C3H7,i-propyl g 2/00 C3H8 g 2/00 C3H8O,1propanol
g 2/00 C3H8O,2propanol g 7/88 C3O2 g tpis *C4
g 7/01 C4H2,butadiyne g 8/00 C4H4,1,3-cyclo- n10/92 C4H6,butadiene
n10/93 C4H6,1butyne n10/93 C4H6,2butyne g 8/00 C4H6,cyclo-
n 4/88 C4H8,1-butene n 4/88 C4H8,cis2-buten n 4/88 C4H8,tr2-butene
n 4/88 C4H8,isobutene g 8/00 C4H8,cyclo- g10/00 (CH3COOH)2
n10/84 C4H9,n-butyl n10/84 C4H9,i-butyl g 1/93 C4H9,s-butyl
g 1/93 C4H9,t-butyl g12/00 C4H10,n-butane g 8/00 C4H10,isobutane
g 8/00 *C5 g 5/90 C5H6,1,3cyclo- g 1/93 C5H8,cyclo-
n 4/87 C5H10,1-pentene g 2/01 C5H10,cyclo- n10/84 C5H11,pentyl
g 1/93 C5H11,t-pentyl n10/85 C5H12,n-pentane n10/85 C5H12,i-pentane
n10/85 CH3C(CH3)2CH3 g 2/93 C6H2 g11/00 C6H5,phenyl
g 8/00 C6H5O,phenoxy g 8/00 C6H6 g 8/00 C6H5OH,phenol
g 1/93 C6H10,cyclo- n 4/87 C6H12,1-hexene g 6/90 C6H12,cyclo-
n10/83 C6H13,n-hexyl g 6/01 C6H14,n-hexane g 7/01 C7H7,benzyl
g 1/93 C7H8 g12/00 C7H8O,cresol-mx n 4/87 C7H14,1-heptene
n10/83 C7H15,n-heptyl n10/85 C7H16,n-heptane n10/85 C7H16,2-methylh
n 4/89 C8H8,styrene n10/86 C8H10,ethylbenz n 4/87 C8H16,1-octene
n10/83 C8H17,n-octyl n 4/85 C8H18,n-octane n 4/85 C8H18,isooctane
n10/83 C9H19,n-nonyl g 3/01 C10H8,naphthale n10/83 C10H21,n-decyl
g 8/00 C12H9,o-bipheny g 8/00 C12H10,biphenyl g 6/97 *H
g 1/01 HCO g 6/01 HCCO g 4/02 HO2
tpis78 *H2 g 5/01 HCHO,formaldehy g 6/01 HCOOH
g 8/89 H2O g 6/99 H2O2 g 6/01 (HCOOH)2
g 5/97 *O g 4/02 *OH tpis89 *O2
g 8/01 O3 n 4/83 C(gr) n 4/83 C(gr)
n 4/83 C(gr) g11/99 H2O(cr) g 8/01 H2O(L)
g 8/01 H2O(L)
SPECIES WITH TRANSPORT PROPERTIES
PURE SPECIES
C CH4 CH3OH CO
CO2 C2H2,acetylene
C2H4 C2H6 C2H5OH H
H2 H2O
O OH O2
BINARY INTERACTIONS
C O
CH4 O2
CO CO2
CO O2
CO2 H2
CO2 H2O
CO2 O2
H H2
H O
H2 H2O
H2 O2
H2O O2
O O2
O/F = 4.000000
EFFECTIVE FUEL EFFECTIVE OXIDANT MIXTURE
ENTHALPY h(2)/R h(1)/R h0/R
(KG-MOL)(K)/KG -0.66898729E+03 -0.48783267E+02 -0.17282407E+03
KG-FORM.WT./KG bi(2) bi(1) b0i
*C 0.62334580E-01 0.00000000E+00 0.12466916E-01
*H 0.24933832E+00 0.00000000E+00 0.49867664E-01
*O 0.00000000E+00 0.62502344E-01 0.50001875E-01
POINT ITN T C H O
1 23 3557.692 -16.600 -10.128 -14.730
Pinf/Pt = 1.727018
2 3 3393.488 -17.013 -10.354 -14.930
Pinf/Pt = 1.724369
2 2 3393.932 -17.012 -10.353 -14.929
3 2 3551.498 -16.615 -10.136 -14.737
3 2 3550.524 -16.618 -10.137 -14.738
3 2 3550.440 -16.618 -10.137 -14.738
4 5 2495.823 -20.267 -12.106 -16.555
4 3 2537.595 -20.065 -12.001 -16.455
4 2 2537.737 -20.064 -12.001 -16.454
5 4 2311.881 -21.234 -12.600 -17.029
5 2 2315.297 -21.215 -12.591 -17.020
6 4 2155.230 -22.177 -13.062 -17.474
6 2 2152.693 -22.194 -13.070 -17.482
THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 1000.0 PSIA
CASE =
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL CH4(L) 1.0000000 -89233.000 111.643
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 4.00000 %FUEL= 20.000000 R,EQ.RATIO= 0.997316 PHI,EQ.RATIO= 0.997316
CHAMBER THROAT EXIT EXIT EXIT EXIT
Pinf/P 1.0000 1.7244 1.0235 62.766 192.59 442.81
P, BAR 68.947 39.984 67.362 1.0985 0.35801 0.15571
T, K 3557.69 3393.93 3550.44 2537.74 2315.30 2152.69
RHO, KG/CU M 5.3817 0 3.3160 0 5.2717 0 1.3176-1 4.7987-2 2.2721-2
H, KJ/KG -1436.95 -2114.16 -1466.72 -5726.21 -6610.98 -7206.66
U, KJ/KG -2718.10 -3319.96 -2744.51 -6559.91 -7357.03 -7891.94
G, KJ/KG -42848.0 -41619.1 -42793.3 -35265.1 -33560.7 -32263.7
S, KJ/(KG)(K) 11.6399 11.6399 11.6399 11.6399 11.6399 11.6399
M, (1/n) 23.089 23.403 23.102 25.309 25.803 26.118
(dLV/dLP)t -1.04396 -1.04042 -1.04381 -1.01772 -1.01150 -1.00748
(dLV/dLT)p 1.7869 1.7607 1.7859 1.4533 1.3238 1.2272
Cp, KJ/(KG)(K) 7.3336 7.3341 7.3347 5.9655 5.0569 4.2825
GAMMAs 1.1272 1.1233 1.1270 1.1094 1.1113 1.1167
SON VEL,M/SEC 1201.7 1163.8 1200.0 961.7 910.6 874.8
MACH NUMBER 0.000 1.000 0.203 3.046 3.533 3.883
TRANSPORT PROPERTIES (GASES ONLY)
CONDUCTIVITY IN UNITS OF MILLIWATTS/(CM)(K)
VISC,MILLIPOISE 1.1505 1.1167 1.1490 0.93374 0.88147 0.84060
WITH EQUILIBRIUM REACTIONS
Cp, KJ/(KG)(K) 7.3336 7.3341 7.3347 5.9655 5.0569 4.2825
CONDUCTIVITY 15.8561 15.2242 15.8307 9.3965 7.2232 5.6368
PRANDTL NUMBER 0.5321 0.5380 0.5323 0.5928 0.6171 0.6386
WITH FROZEN REACTIONS
Cp, KJ/(KG)(K) 2.2105 2.2007 2.2101 2.1277 2.0981 2.0718
CONDUCTIVITY 3.6960 3.5487 3.6895 2.7499 2.5242 2.3503
PRANDTL NUMBER 0.6881 0.6925 0.6883 0.7225 0.7327 0.7410
PERFORMANCE PARAMETERS
Ae/At 1.0000 3.0000 10.000 25.000 50.000
CSTAR, M/SEC 1786.6 1786.6 1786.6 1786.6 1786.6
CF 0.6514 0.1366 1.6394 1.8006 1.9014
Ivac, M/SEC 2199.9 5480.7 3213.6 3448.8 3598.7
Isp, M/SEC 1163.8 244.0 2928.9 3216.8 3397.0
MOLE FRACTIONS
*CO 0.13286 0.12417 0.13250 0.05890 0.03869 0.02516
*CO2 0.15496 0.16758 0.15549 0.25662 0.28300 0.30045
COOH 0.00001 0.00001 0.00001 0.00000 0.00000 0.00000
*H 0.01785 0.01546 0.01774 0.00416 0.00215 0.00111
HCO 0.00001 0.00000 0.00001 0.00000 0.00000 0.00000
HO2 0.00027 0.00018 0.00026 0.00001 0.00000 0.00000
*H2 0.04857 0.04486 0.04841 0.02164 0.01499 0.01039
H2O 0.47378 0.49142 0.47454 0.59375 0.61921 0.63536
H2O2 0.00004 0.00002 0.00004 0.00000 0.00000 0.00000
*O 0.01754 0.01481 0.01742 0.00309 0.00141 0.00066
*OH 0.08847 0.07877 0.08805 0.02717 0.01620 0.00984
*O2 0.06563 0.06271 0.06551 0.03466 0.02435 0.01702
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
*C *CH CH2 CH3 CH2OH
CH3O CH4 CH3OH CH3OOH *C2
C2H C2H2,acetylene C2H2,vinylidene CH2CO,ketene O(CH)2O
HO(CO)2OH C2H3,vinyl CH3CO,acetyl C2H4 C2H4O,ethylen-o
CH3CHO,ethanal CH3COOH OHCH2COOH C2H5 C2H6
C2H5OH CH3OCH3 CH3O2CH3 C2O *C3
C3H3,1-propynl C3H3,2-propynl C3H4,allene C3H4,propyne C3H4,cyclo-
C3H5,allyl C3H6,propylene C3H6,cyclo- C3H6O,propylox C3H6O,acetone
C3H6O,propanal C3H7,n-propyl C3H7,i-propyl C3H8 C3H8O,1propanol
C3H8O,2propanol C3O2 *C4 C4H2,butadiyne C4H4,1,3-cyclo-
C4H6,butadiene C4H6,1butyne C4H6,2butyne C4H6,cyclo- C4H8,1-butene
C4H8,cis2-buten C4H8,tr2-butene C4H8,isobutene C4H8,cyclo- (CH3COOH)2
C4H9,n-butyl C4H9,i-butyl C4H9,s-butyl C4H9,t-butyl C4H10,n-butane
C4H10,isobutane *C5 C5H6,1,3cyclo- C5H8,cyclo- C5H10,1-pentene
C5H10,cyclo- C5H11,pentyl C5H11,t-pentyl C5H12,n-pentane C5H12,i-pentane
CH3C(CH3)2CH3 C6H2 C6H5,phenyl C6H5O,phenoxy C6H6
C6H5OH,phenol C6H10,cyclo- C6H12,1-hexene C6H12,cyclo- C6H13,n-hexyl
C6H14,n-hexane C7H7,benzyl C7H8 C7H8O,cresol-mx C7H14,1-heptene
C7H15,n-heptyl C7H16,n-heptane C7H16,2-methylh C8H8,styrene C8H10,ethylbenz
C8H16,1-octene C8H17,n-octyl C8H18,n-octane C8H18,isooctane C9H19,n-nonyl
C10H8,naphthale C10H21,n-decyl C12H9,o-bipheny C12H10,biphenyl HCCO
HCHO,formaldehy HCOOH (HCOOH)2 O3 C(gr)
H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION
Pin = 1000.0 PSIA
CASE =
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL CH4(L) 1.0000000 -89233.000 111.643
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 4.00000 %FUEL= 20.000000 R,EQ.RATIO= 0.997316 PHI,EQ.RATIO= 0.997316
CHAMBER THROAT EXIT EXIT EXIT EXIT
Pinf/P 1.0000 1.7701 1.0246 82.428 280.86 703.69
P, BAR 68.947 38.952 67.290 0.83646 0.24549 0.09798
T, K 3557.69 3239.98 3543.62 1662.93 1316.52 1095.00
RHO, KG/CU M 5.3817 0 3.3385 0 5.2732 0 1.3968-1 5.1781-2 2.4848-2
H, KJ/KG -1436.95 -2135.40 -1468.05 -5426.89 -6082.29 -6480.25
U, KJ/KG -2718.10 -3302.14 -2744.14 -6025.72 -6556.38 -6874.57
G, KJ/KG -42848.0 -39848.4 -42715.3 -24783.2 -21406.4 -19225.9
S, KJ/(KG)(K) 11.6399 11.6399 11.6399 11.6399 11.6399 11.6399
M, (1/n) 23.089 23.089 23.089 23.089 23.089 23.089
Cp, KJ/(KG)(K) 2.2105 2.1856 2.2095 1.9424 1.8369 1.7542
GAMMAs 1.1946 1.1973 1.1947 1.2276 1.2439 1.2583
SON VEL,M/SEC 1237.1 1181.9 1234.7 857.4 767.9 704.4
MACH NUMBER 0.000 1.000 0.202 3.295 3.969 4.509
TRANSPORT PROPERTIES (GASES ONLY)
CONDUCTIVITY IN UNITS OF MILLIWATTS/(CM)(K)
VISC,MILLIPOISE 1.1505 1.0765 1.1472 0.65977 0.55045 0.47460
WITH FROZEN REACTIONS
Cp, KJ/(KG)(K) 2.2105 2.1856 2.2095 1.9424 1.8369 1.7542
CONDUCTIVITY 3.6960 3.3996 3.6831 1.7500 1.3515 1.0969
PRANDTL NUMBER 0.6881 0.6921 0.6882 0.7323 0.7481 0.7590
PERFORMANCE PARAMETERS
Ae/At 1.0000 3.0000 10.000 25.000 50.000
CSTAR, M/SEC 1747.4 1747.4 1747.4 1747.4 1747.4
CF 0.6764 0.1427 1.6166 1.7444 1.8176
Ivac, M/SEC 2169.1 5365.7 3036.9 3203.6 3300.1
Isp, M/SEC 1181.9 249.4 2824.9 3048.1 3175.9
MOLE FRACTIONS
*CO 0.13286 *CO2 0.15496 COOH 0.00001
*H 0.01785 HCO 0.00001 HO2 0.00027
*H2 0.04857 H2O 0.47378 H2O2 0.00004
*O 0.01754 *OH 0.08847 *O2 0.06563
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
*C *CH CH2 CH3 CH2OH
CH3O CH4 CH3OH CH3OOH *C2
C2H C2H2,acetylene C2H2,vinylidene CH2CO,ketene O(CH)2O
HO(CO)2OH C2H3,vinyl CH3CO,acetyl C2H4 C2H4O,ethylen-o
CH3CHO,ethanal CH3COOH OHCH2COOH C2H5 C2H6
C2H5OH CH3OCH3 CH3O2CH3 C2O *C3
C3H3,1-propynl C3H3,2-propynl C3H4,allene C3H4,propyne C3H4,cyclo-
C3H5,allyl C3H6,propylene C3H6,cyclo- C3H6O,propylox C3H6O,acetone
C3H6O,propanal C3H7,n-propyl C3H7,i-propyl C3H8 C3H8O,1propanol
C3H8O,2propanol C3O2 *C4 C4H2,butadiyne C4H4,1,3-cyclo-
C4H6,butadiene C4H6,1butyne C4H6,2butyne C4H6,cyclo- C4H8,1-butene
C4H8,cis2-buten C4H8,tr2-butene C4H8,isobutene C4H8,cyclo- (CH3COOH)2
C4H9,n-butyl C4H9,i-butyl C4H9,s-butyl C4H9,t-butyl C4H10,n-butane
C4H10,isobutane *C5 C5H6,1,3cyclo- C5H8,cyclo- C5H10,1-pentene
C5H10,cyclo- C5H11,pentyl C5H11,t-pentyl C5H12,n-pentane C5H12,i-pentane
CH3C(CH3)2CH3 C6H2 C6H5,phenyl C6H5O,phenoxy C6H6
C6H5OH,phenol C6H10,cyclo- C6H12,1-hexene C6H12,cyclo- C6H13,n-hexyl
C6H14,n-hexane C7H7,benzyl C7H8 C7H8O,cresol-mx C7H14,1-heptene
C7H15,n-heptyl C7H16,n-heptane C7H16,2-methylh C8H8,styrene C8H10,ethylbenz
C8H16,1-octene C8H17,n-octyl C8H18,n-octane C8H18,isooctane C9H19,n-nonyl
C10H8,naphthale C10H21,n-decyl C12H9,o-bipheny C12H10,biphenyl HCCO
HCHO,formaldehy HCOOH (HCOOH)2 O3 C(gr)
H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
RPA Lite
RPA 결과
# Engine name: Traditional Example
# 금 1 23 11:05:02 2026
#
#***************************************************************************************************
# Propellant Specification
#---------------------------------------------------------------------------------------------------
# Component Temp. Mass Mole
# [K] fraction fraction
#---------------------------------------------------------------------------------------------------
# CH4(L) 111.6 0.2000000 0.3327363
# O2(L) 90.2 0.8000000 0.6672637
#---------------------------------------------------------------------------------------------------
# Total: 1.0000000 1.0000000
#---------------------------------------------------------------------------------------------------
# Exploded formula: (O)1.335 (C)0.333 (H)1.331
# O/F: 4.0000000
# O/F 0: 3.9892635 (stoichiometric)
# alpha: 1.0026914 (oxidizer excess coefficient)
#---------------------------------------------------------------------------------------------------
#
# Table 1. Thermodynamic properties
#---------------------------------------------------------------------------------------------------
# Parameter Injector Nozzle inl Nozzle thr Nozzle exi Unit
#---------------------------------------------------------------------------------------------------
Pressure 6.8948 6.5895 3.9109 0.1074 MPa
Temperature 3557.6911 3547.4503 3391.2186 2536.5837 K
Enthalpy -1436.9475 -1466.5308 -2113.7632 -5724.6039 kJ/kg
Entropy 11.6398 11.6478 11.6478 11.6478 kJ/(kg·K)
Internal energy -2718.0942 -2743.6315 -3318.9297 -6558.0750 kJ/kg
Specific heat (p=const) 7.3336 7.3549 7.3542 5.9827 kJ/(kg·K)
Specific heat (V=const) 6.2322 6.2520 6.2927 5.2991 kJ/(kg·K)
Gamma 1.1767 1.1764 1.1687 1.1290
Isentropic exponent 1.1272 1.1269 1.1232 1.1093
Gas constant 0.3601 0.3600 0.3554 0.3286 kJ/(kg·K)
Molecular weight (M) 23.0889 23.0954 23.3961 25.3042
Molecular weight (MW) 0.0231 0.0231 0.0234 0.0253
Density 5.3817 5.1597 3.2451 0.1289 kg/m³
Sonic velocity 1201.7002 1199.6595 1163.4572 961.5358 m/s
Velocity 0.0000 243.2418 1163.4572 2928.3635 m/s
Mach number 0.0000 0.2028 1.0000 3.0455
Area ratio 3.0000 3.0000 1.0000 10.0000
Mass flux 1255.0541 1255.0541 3775.5682 377.4064 kg/(m²·s)
Mass flux (relative) 0.0002 0.0002 0.0000 0.0000 kg/(N·s)
#---------------------------------------------------------------------------------------------------
#
#---------------------------------------------------------------------------------------------------
#
# Table 2. Fractions of the combustion products
#---------------------------------------------------------------------------------------------------
# Species Injector Injector Nozzle inl Nozzle inl Nozzle thr Nozzle thr Nozzle exi Nozzle exi
# mass fract mole fract mass fract mole fract mass fract mole fract mass fract mole fract
#---------------------------------------------------------------------------------------------------
CO 0.1611792 0.1328612 0.1608713 0.1326447 0.1488345 0.1243175 0.0653872 0.0590706
CO2 0.2953737 0.1549635 0.2958591 0.1552617 0.3147894 0.1673467 0.4459260 0.2563951
COOH 0.0000266 0.0000137 0.0000256 0.0000131 0.0000153 0.0000080 0.0000003 0.0000002
H 0.0007793 0.0178508 0.0007788 0.0178440 0.0006700 0.0155508 0.0001672 0.0041966
H2 0.0042407 0.0485714 0.0042354 0.0485236 0.0038747 0.0449697 0.0017302 0.0217184
H2O 0.3696707 0.4737814 0.3698692 0.4741688 0.3781239 0.4910623 0.4225333 0.5934899
H2O2 0.0000528 0.0000358 0.0000511 0.0000347 0.0000330 0.0000227 0.0000012 0.0000009
HCHO,formaldehy 0.0000002 0.0000002 0.0000002 0.0000002 0.0000000 0.0000000 0.0000000 0.0000000
HCO 0.0000096 0.0000077 0.0000093 0.0000074 0.0000050 0.0000040 0.0000000 0.0000000
HCOOH 0.0000034 0.0000017 0.0000032 0.0000016 0.0000018 0.0000009 0.0000000 0.0000000
HO2 0.0003824 0.0002675 0.0003730 0.0002610 0.0002573 0.0001824 0.0000136 0.0000104
O 0.0121573 0.0175444 0.0121223 0.0174987 0.0101720 0.0148746 0.0019677 0.0031121
O2 0.0909552 0.0656293 0.0909012 0.0656087 0.0859024 0.0628080 0.0439663 0.0347680
O3 0.0000012 0.0000006 0.0000012 0.0000006 0.0000006 0.0000003 0.0000000 0.0000000
OH 0.0651677 0.0884708 0.0648993 0.0881311 0.0573200 0.0788521 0.0183070 0.0272379
#---------------------------------------------------------------------------------------------------
#
#---------------------------------------------------------------------------------------------------
#
# Table 3. Theoretical (ideal) performance
#---------------------------------------------------------------------------------------------------
# Parameter Sea level Optimum ex Vacuum Unit
#---------------------------------------------------------------------------------------------------
Characteristic velocity 0.0000 1786.1300 0.0000 m/s
Effective exhaust velocity 2944.5100 2928.3600 3212.9800 m/s
Specific impulse (by mass) 2944.5100 2928.3600 3212.9800 N·s/kg
Specific impulse (by weight) 300.2600 298.6100 327.6300 s
Thrust coefficient 1.6485 1.6395 1.7988
#---------------------------------------------------------------------------------------------------
#
#---------------------------------------------------------------------------------------------------
#
# Table 4. Estimated delivered performance
#---------------------------------------------------------------------------------------------------
# Parameter Sea level Optimum ex Vacuum Unit
#---------------------------------------------------------------------------------------------------
Characteristic velocity 0.0000 1743.9100 0.0000 m/s
Effective exhaust velocity 2793.6300 2777.4900 3062.1100 m/s
Specific impulse (by mass) 2793.6300 2777.4900 3062.1100 N·s/kg
Specific impulse (by weight) 284.8700 283.2200 312.2500 s
Thrust coefficient 1.6019 1.5927 1.7559
#---------------------------------------------------------------------------------------------------
#
#<b>Ambient condition for optimum expansion:</b> H=0.00 km, p=1.060 atm
#
#
#---------------------------------------------------------------------------------------------------
#
#
#---------------------------------------------------------------------------------------------------
# Engine name: Traditional Example
# 금 1 23 11:09:17 2026
#
#************************************************************************************************************************************************************************************
# Results of nested analysis
#------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
# Ratio, O/F pc, psi Nozzle inl Nozzle exi rho, kg/m^ Tc, K M gamma k c*, m/s Is opt, s Is vac, s Cf opt Cf vac c.factor
#------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
4.0000 1000.0000 3.0000 10.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 298.6100 327.6331 1.6395 1.7988 1.0000
4.0000 1000.0000 3.0000 15.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 312.4513 338.8546 1.7155 1.8605 1.0000
4.0000 1000.0000 3.0000 20.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 321.4240 346.2143 1.7648 1.9009 1.0000
4.0000 1000.0000 3.0000 25.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 327.9674 351.6173 1.8007 1.9305 1.0000
4.0000 1000.0000 3.0000 30.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 333.0702 355.8492 1.8287 1.9538 1.0000
4.0000 1000.0000 3.0000 35.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 337.2265 359.3063 1.8515 1.9727 1.0000
4.0000 1000.0000 3.0000 40.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 340.7167 362.2157 1.8707 1.9887 1.0000
4.0000 1000.0000 3.0000 45.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 343.7146 364.7187 1.8871 2.0025 1.0000
4.0000 1000.0000 3.0000 50.0000 765.7519 3557.6911 23.0889 1.1767 1.1272 1786.1343 346.3350 366.9089 1.9015 2.0145 1.0000
#*********************************************************************************************************************************************************************
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