THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM
COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR
Pin = 145.0 PSIA
CASE = A0013027
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL C3H8 1.0000000 -104680.000 298.150
OXIDANT N2O 1.0000000 82050.000 298.150
O/F= <strong>1.00000</strong> %FUEL= 50.000000 R,EQ.RATIO= 9.981218 PHI,EQ.RATIO= 9.981218
CHAMBER THROAT EXIT
Pinf/P 1.0000 1.7412 7.6741
P, BAR <strong>10.000</strong> 5.7431 1.3031
T, K <strong>1112.65</strong> 1048.05 905.83
RHO, KG/CU M 1.8297 0 1.1323 0 3.0939-1
H, KJ/KG -254.85 -546.82 -1232.49
U, KJ/KG -801.38 -1054.04 -1653.68
G, KJ/KG -13637.6 -13152.6 -12127.7
S, KJ/(KG)(K) 12.0279 12.0279 12.0279
M, (1/n) 16.927 17.180 17.882
MW, MOL WT 12.526 12.545 12.595
(dLV/dLP)t -1.08544 -1.08763 -1.08553
(dLV/dLT)p 2.0032 2.0963 2.1982
Cp, KJ/(KG)(K) 8.8214 9.7093 10.8825
GAMMAs 1.1601 1.1513 1.1376
SON VEL,M/SEC 796.3 764.2 692.2
MACH NUMBER 0.000 1.000 2.020
PERFORMANCE PARAMETERS
Ae/At 1.0000 2.0000
CSTAR, M/SEC <strong>1155.8</strong> 1155.8
CF 0.6612 1.2099
Ivac, M/SEC 1427.9 1699.5
Isp, M/SEC 764.2 <strong>1398.3</strong>
MOLE FRACTIONS
CH4 6.8076-2 6.8949-2 7.1295-2
*CO 9.0176-2 7.7497-2 4.4125-2
*CO2 7.8578-3 1.0473-2 1.7350-2
*H2 3.9500-1 3.8654-1 3.6414-1
H2O 3.6412-2 4.4069-2 6.4256-2
NH3 3.7643-4 3.0726-4 1.7827-4
*N2 1.4211-1 1.4236-1 1.4299-1
C(gr) 2.5998-1 2.6980-1 2.9567-1
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K