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*******************************************************************************
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 rocket equilibrium o/f=5.55157,6.5
case=8 p,bar=53.3172 subar=1.58,pi/p=10,100,1000,supar=25,50,75
reactants
fuel = H2(L) wt% 100. t(k) 20.27
oxid = O2(L) wt% 100. t(k) 90.17
output siunits
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=F EQL=T IONS=F SIUNIT=T DEBUGF=F SHKDBG=F DETDBG=F TRNSPT=F
TRACE= 0.00E+00 S/R= 0.000000E+00 H/R= 0.000000E+00 U/R= 0.000000E+00
Pc,BAR = 53.317200
Pc/P = 10.0000 100.0000 1000.0000
SUBSONIC AREA RATIOS = 1.5800
SUPERSONIC AREA RATIOS = 25.0000 50.0000 75.0000
NFZ= 1 Mdot/Ac= 0.000000E+00 Ac/At= 0.000000E+00
REACTANT WT.FRAC (ENERGY/R),K TEMP,K DENSITY
EXPLODED FORMULA
F: H2(L) 1.000000 -0.108389E+04 20.27 0.0000
H 2.00000
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: 5/03/02
g 6/97 *H g 4/02 HO2 tpis78 *H2
g 8/89 H2O g 6/99 H2O2 g 5/97 *O
g 4/02 *OH tpis89 *O2 g 8/01 O3
g11/99 H2O(cr) g 8/01 H2O(L) g 8/01 H2O(L)
O/F = 5.551570
EFFECTIVE FUEL EFFECTIVE OXIDANT MIXTURE
ENTHALPY h(2)/R h(1)/R h0/R
(KG-MOL)(K)/KG -0.53767500E+03 -0.48783267E+02 -0.12340534E+03
KG-FORM.WT./KG bi(2) bi(1) b0i
*H 0.99212255E+00 0.00000000E+00 0.15143279E+00
*O 0.00000000E+00 0.62502344E-01 0.52962288E-01
POINT ITN T H O
1 9 3383.845 -9.262 -16.577
Pinf/Pt = 1.737750
2 4 3185.977 -9.430 -16.983
Pinf/Pt = 1.739241
2 2 3185.673 -9.430 -16.983
3 4 2567.340 -9.921 -18.808
4 4 1759.893 -10.455 -23.527
5 4 1115.867 -10.959 -32.655
6 3 3354.871 -9.287 -16.632
6 2 3349.365 -9.291 -16.643
6 2 3348.695 -9.292 -16.644
6 1 3348.687 -9.292 -16.644
7 5 1441.980 -10.683 -26.970
7 2 1468.156 -10.663 -26.627
8 3 1242.708 -10.845 -30.076
8 2 1219.614 -10.865 -30.504
THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 773.3 PSIA
CASE = 8
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL H2(L) 1.0000000 -9012.000 20.270
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 5.55157 %FUEL= 15.263517 R,EQ.RATIO= 1.429629 PHI,EQ.RATIO= 1.429629
CHAMBER THROAT EXIT EXIT EXIT EXIT EXIT EXIT
Pinf/P 1.0000 1.7392 10.000 100.00 1000.00 1.1020 260.19 654.48
P, BAR 53.317 30.655 5.3317 0.53317 0.05332 48.382 0.20491 0.08146
T, K 3383.84 3185.67 2567.34 1759.89 1115.87 3348.69 1468.16 1219.61
RHO, KG/CU M 2.4097 0 1.4864 0 3.2778-1 4.8118-2 7.5898-3 2.2137 0 2.2170-2 1.0610-2
H, KJ/KG -1026.05 -2208.65 -5428.75 -8561.51 -10621.8 -1239.65 -9531.45 -10310.3
U, KJ/KG -3238.68 -4271.01 -7055.36 -9669.56 -11324.3 -3425.26 -10455.7 -11078.1
G, KJ/KG -64163.7 -61648.7 -53331.6 -41398.6 -31442.3 -63721.3 -36925.1 -33066.6
S, KJ/(KG)(K) 18.6586 18.6586 18.6586 18.6586 18.6586 18.6586 18.6586 18.6586
M, (1/n) 12.716 12.843 13.123 13.206 13.207 12.739 13.207 13.207
(dLV/dLP)t -1.02010 -1.01475 -1.00325 -1.00006 -1.00000 -1.01912 -1.00000 -1.00000
(dLV/dLT)p 1.3658 1.2844 1.0761 1.0018 1.0000 1.3515 1.0001 1.0000
Cp, KJ/(KG)(K) 8.3253 7.4796 4.8799 3.4348 2.9626 8.1823 3.2234 3.0420
GAMMAs 1.1447 1.1468 1.1725 1.2253 1.2698 1.1449 1.2428 1.2610
SON VEL,M/SEC 1591.5 1537.9 1381.0 1165.2 944.5 1581.9 1071.8 984.0
MACH NUMBER 0.000 1.000 2.149 3.332 4.638 0.413 3.848 4.379
PERFORMANCE PARAMETERS
Ae/At 1.0000 2.3503 12.238 68.753 1.5800 25.000 50.000
CSTAR, M/SEC 2332.3 2332.3 2332.3 2332.3 2332.3 2332.3 2332.3
CF 0.6594 1.2723 1.6645 1.8783 0.2802 1.7684 1.8476
Ivac, M/SEC 2878.9 3515.5 4167.6 4541.2 3997.6 4348.5 4487.3
Isp, M/SEC 1537.9 2967.4 3882.1 4380.8 653.6 4124.4 4309.1
MOLE FRACTIONS
*H 0.03350 0.02652 0.00793 0.00019 0.00000 0.03226 0.00001 0.00000
HO2 0.00001 0.00001 0.00000 0.00000 0.00000 0.00001 0.00000 0.00000
*H2 0.29479 0.29432 0.29711 0.30040 0.30052 0.29466 0.30051 0.30052
H2O 0.63456 0.65280 0.69030 0.69937 0.69948 0.63794 0.69948 0.69948
H2O2 0.00001 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
*O 0.00207 0.00120 0.00007 0.00000 0.00000 0.00190 0.00000 0.00000
*OH 0.03334 0.02409 0.00452 0.00003 0.00000 0.03164 0.00000 0.00000
*O2 0.00172 0.00104 0.00007 0.00000 0.00000 0.00159 0.00000 0.00000
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
O3 H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
3 3 1067.700 -11.005 -33.799
3 2 1088.644 -10.984 -33.289
THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 773.3 PSIA
CASE = 8
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL H2(L) 1.0000000 -9012.000 20.270
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 5.55157 %FUEL= 15.263517 R,EQ.RATIO= 1.429629 PHI,EQ.RATIO= 1.429629
CHAMBER THROAT EXIT
Pinf/P 1.0000 1.7392 1122.79
P, BAR 53.317 30.655 0.04749
T, K 3383.84 3185.67 1088.64
RHO, KG/CU M 2.4097 0 1.4864 0 6.9287-3
H, KJ/KG -1026.05 -2208.65 -10702.2
U, KJ/KG -3238.68 -4271.01 -11387.5
G, KJ/KG -64163.7 -61648.7 -31014.7
S, KJ/(KG)(K) 18.6586 18.6586 18.6586
M, (1/n) 12.716 12.843 13.207
(dLV/dLP)t -1.02010 -1.01475 -1.00000
(dLV/dLT)p 1.3658 1.2844 1.0000
Cp, KJ/(KG)(K) 8.3253 7.4796 2.9416
GAMMAs 1.1447 1.1468 1.2723
SON VEL,M/SEC 1591.5 1537.9 933.8
MACH NUMBER 0.000 1.000 4.711
PERFORMANCE PARAMETERS
Ae/At 1.0000 75.000
CSTAR, M/SEC 2332.3 2332.3
CF 0.6594 1.8861
Ivac, M/SEC 2878.9 4554.9
Isp, M/SEC 1537.9 4399.1
MOLE FRACTIONS
*H 0.03350 0.02652 0.00000
HO2 0.00001 0.00001 0.00000
*H2 0.29479 0.29432 0.30052
H2O 0.63456 0.65280 0.69948
H2O2 0.00001 0.00000 0.00000
*O 0.00207 0.00120 0.00000
*OH 0.03334 0.02409 0.00000
*O2 0.00172 0.00104 0.00000
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
O3 H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
O/F = 6.500000
EFFECTIVE FUEL EFFECTIVE OXIDANT MIXTURE
ENTHALPY h(2)/R h(1)/R h0/R
(KG-MOL)(K)/KG -0.53767500E+03 -0.48783267E+02 -0.11396883E+03
KG-FORM.WT./KG bi(2) bi(1) b0i
*H 0.99212255E+00 0.00000000E+00 0.13228301E+00
*O 0.00000000E+00 0.62502344E-01 0.54168698E-01
POINT ITN T H O
1 4 3508.779 -9.513 -15.889
Pinf/Pt = 1.730918
2 4 3331.285 -9.707 -16.179
Pinf/Pt = 1.729851
2 2 3331.480 -9.706 -16.179
3 5 2801.738 -10.312 -17.388
4 5 2073.618 -10.967 -20.553
5 4 1380.504 -11.501 -27.164
6 3 3482.572 -9.541 -15.929
6 2 3477.571 -9.547 -15.937
6 2 3476.959 -9.547 -15.938
6 1 3476.951 -9.547 -15.938
7 6 1743.194 -11.210 -23.010
7 3 1805.110 -11.164 -22.476
7 1 1805.146 -11.164 -22.476
8 3 1534.910 -11.372 -25.143
8 2 1535.446 -11.372 -25.137
THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 773.3 PSIA
CASE = 8
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL H2(L) 1.0000000 -9012.000 20.270
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 6.50000 %FUEL= 13.333333 R,EQ.RATIO= 1.221028 PHI,EQ.RATIO= 1.221028
CHAMBER THROAT EXIT EXIT EXIT EXIT EXIT EXIT
Pinf/P 1.0000 1.7299 10.000 100.00 1000.00 1.1011 230.07 567.85
P, BAR 53.317 30.822 5.3317 0.53317 0.05332 48.423 0.23174 0.09389
T, K 3508.78 3331.48 2801.74 2073.62 1380.50 3476.95 1805.15 1535.45
RHO, KG/CU M 2.5873 0 1.5948 0 3.3906-1 4.6697-2 7.0229-3 2.3765 0 2.3339-2 1.1119-2
H, KJ/KG -947.59 -2041.42 -5107.57 -8230.48 -10401.5 -1144.91 -9119.16 -9948.03
U, KJ/KG -3008.36 -3974.08 -6680.05 -9372.24 -11160.7 -3182.46 -10112.1 -10792.4
G, KJ/KG -61824.1 -59841.8 -53717.1 -44207.3 -34352.9 -61469.2 -40438.0 -36587.7
S, KJ/(KG)(K) 17.3498 17.3498 17.3498 17.3498 17.3498 17.3498 17.3498 17.3498
M, (1/n) 14.157 14.332 14.814 15.101 15.119 14.188 15.116 15.119
(dLV/dLP)t -1.03428 -1.02842 -1.01111 -1.00062 -1.00000 -1.03325 -1.00011 -1.00001
(dLV/dLT)p 1.6066 1.5303 1.2466 1.0180 1.0001 1.5939 1.0036 1.0004
Cp, KJ/(KG)(K) 9.9678 9.3693 6.5786 3.5348 2.8742 9.8735 3.1867 2.9799
GAMMAs 1.1335 1.1319 1.1383 1.1916 1.2366 1.1332 1.2103 1.2265
SON VEL,M/SEC 1528.4 1479.1 1337.9 1166.4 968.9 1519.5 1096.2 1017.7
MACH NUMBER 0.000 1.000 2.156 3.272 4.488 0.413 3.688 4.169
PERFORMANCE PARAMETERS
Ae/At 1.0000 2.4119 13.235 77.243 1.5800 25.000 50.000
CSTAR, M/SEC 2260.3 2260.3 2260.3 2260.3 2260.3 2260.3 2260.3
CF 0.6544 1.2761 1.6885 1.9237 0.2779 1.7885 1.8770
Ivac, M/SEC 2785.7 3429.6 4115.7 4522.9 3871.7 4288.3 4441.8
Isp, M/SEC 1479.1 2884.4 3816.5 4348.3 628.2 4042.7 4242.7
MOLE FRACTIONS
*H 0.03730 0.03175 0.01531 0.00154 0.00001 0.03631 0.00033 0.00004
HO2 0.00006 0.00003 0.00000 0.00000 0.00000 0.00005 0.00000 0.00000
*H2 0.20382 0.19812 0.18384 0.18050 0.18101 0.20280 0.18087 0.18100
H2O 0.68289 0.70848 0.77840 0.81706 0.81898 0.68747 0.81868 0.81896
H2O2 0.00001 0.00001 0.00000 0.00000 0.00000 0.00001 0.00000 0.00000
*O 0.00613 0.00447 0.00095 0.00000 0.00000 0.00582 0.00000 0.00000
*OH 0.06190 0.05093 0.01989 0.00089 0.00000 0.05994 0.00011 0.00001
*O2 0.00790 0.00620 0.00161 0.00001 0.00000 0.00760 0.00000 0.00000
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
O3 H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
3 3 1391.129 -11.492 -27.010
3 2 1390.656 -11.493 -27.017
THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 773.3 PSIA
CASE = 8
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL H2(L) 1.0000000 -9012.000 20.270
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 6.50000 %FUEL= 13.333333 R,EQ.RATIO= 1.221028 PHI,EQ.RATIO= 1.221028
CHAMBER THROAT EXIT
Pinf/P 1.0000 1.7299 962.39
P, BAR 53.317 30.822 0.05540
T, K 3508.78 3331.48 1390.66
RHO, KG/CU M 2.5873 0 1.5948 0 7.2441-3
H, KJ/KG -947.59 -2041.42 -10372.3
U, KJ/KG -3008.36 -3974.08 -11137.0
G, KJ/KG -61824.1 -59841.8 -34499.8
S, KJ/(KG)(K) 17.3498 17.3498 17.3498
M, (1/n) 14.157 14.332 15.119
(dLV/dLP)t -1.03428 -1.02842 -1.00000
(dLV/dLT)p 1.6066 1.5303 1.0001
Cp, KJ/(KG)(K) 9.9678 9.3693 2.8812
GAMMAs 1.1335 1.1319 1.2359
SON VEL,M/SEC 1528.4 1479.1 972.2
MACH NUMBER 0.000 1.000 4.466
PERFORMANCE PARAMETERS
Ae/At 1.0000 75.000
CSTAR, M/SEC 2260.3 2260.3
CF 0.6544 1.9208
Ivac, M/SEC 2785.7 4517.7
Isp, M/SEC 1479.1 4341.6
MOLE FRACTIONS
*H 0.03730 0.03175 0.00001
HO2 0.00006 0.00003 0.00000
*H2 0.20382 0.19812 0.18101
H2O 0.68289 0.70848 0.81898
H2O2 0.00001 0.00001 0.00000
*O 0.00613 0.00447 0.00000
*OH 0.06190 0.05093 0.00000
*O2 0.00790 0.00620 0.00000
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
O3 H2O(cr) H2O(L)
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS
|
