******************************************************************************* NASA-LEWIS CHEMICAL EQUILIBRIUM PROGRAM CEA, AUGUST 1995 BY BONNIE MCBRIDE AND SANFORD GORDON REFS: NASA RP-1311, OCTOBER 1994 AND NASA RP- ******************************************************************************* #E4.inp #LOX Ethanol Script for Rocket Team engine E4 #Written by: Carl Dietrich problem rocket case=1 p,psi=130, pi/p=10, eql, frozen, nfz=1, o/f=1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9 2.0 2.1 2.2 2.3 2.4 2.5, reactants fuel = C2H5OH(L) , wt% 100, t(k) 298 oxid = O2(L) , wt% 100, t(k) 90 output siunits short end THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.00000 %FUEL= 50.000000 R,EQ.RATIO= 1.804392 PHI,EQ.RATIO= 2.083751 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7918 10.000 P, BAR 8.9632 5.0023 0.89632 T, K 2349.25 2110.31 1513.26 RHO, KG/CU M 8.4448-1 5.2512-1 1.3127-1 H, KJ/KG -3214.88 -3801.81 -5196.40 U, KJ/KG -4276.26 -4754.41 -5879.19 G, KJ/KG -34203.0 -31638.2 -25157.3 S, KJ/(KG)(K) 13.1906 13.1906 13.1906 M, (1/n) 18.403 18.419 18.428 (dLV/dLP)t -1.00066 -1.00023 -1.00000 (dLV/dLT)p 1.0161 1.0060 1.0001 Cp, KJ/(KG)(K) 2.5546 2.4206 2.2997 GAMMAs 1.2224 1.2323 1.2442 SON VEL,M/SEC 1139.0 1083.5 921.7 MACH NUMBER 0.000 1.000 2.160 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1771 CSTAR, M/SEC 1575.4 1575.4 CF 0.6877 1.2636 Ivac, M/SEC 1962.7 2333.7 Isp, M/SEC 1083.4 1990.7 MOLE FRACTIONS *CO 0.33594 0.33038 0.30168 *CO2 0.06353 0.06943 0.09832 *H 0.00223 0.00081 0.00001 *H2 0.28644 0.29310 0.32242 H2O 0.31144 0.30618 0.27756 *OH 0.00042 0.00010 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.00000 %FUEL= 50.000000 R,EQ.RATIO= 1.804392 PHI,EQ.RATIO= 2.083751 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7988 10.000 P, BAR 8.9632 4.9828 0.89632 T, K 2349.25 2096.04 1479.56 RHO, KG/CU M 8.4448-1 5.2617-1 1.3409-1 H, KJ/KG -3214.88 -3803.95 -5178.53 U, KJ/KG -4276.26 -4750.93 -5846.99 G, KJ/KG -34203.0 -31452.0 -24694.9 S, KJ/(KG)(K) 13.1906 13.1906 13.1906 M, (1/n) 18.403 18.403 18.403 Cp, KJ/(KG)(K) 2.3487 2.3025 2.1447 GAMMAs 1.2382 1.2441 1.2669 SON VEL,M/SEC 1146.4 1085.4 920.3 MACH NUMBER 0.000 1.000 2.153 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1493 CSTAR, M/SEC 1569.4 1569.4 CF 0.6916 1.2627 Ivac, M/SEC 1957.9 2319.1 Isp, M/SEC 1085.4 1981.7 MOLE FRACTIONS *CO 0.33594 *CO2 0.06353 *H 0.00223 *H2 0.28644 H2O 0.31144 *OH 0.00042 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.10000 %FUEL= 47.619047 R,EQ.RATIO= 1.679718 PHI,EQ.RATIO= 1.894319 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7795 10.000 P, BAR 8.9632 5.0370 0.89632 T, K 2592.92 2356.23 1718.78 RHO, KG/CU M 8.0111-1 4.9660-1 1.2135-1 H, KJ/KG -3081.10 -3695.55 -5199.24 U, KJ/KG -4199.94 -4709.86 -5937.86 G, KJ/KG -36904.3 -34431.2 -27619.8 S, KJ/(KG)(K) 13.0445 13.0445 13.0445 M, (1/n) 19.269 19.315 19.348 (dLV/dLP)t -1.00210 -1.00090 -1.00003 (dLV/dLT)p 1.0474 1.0219 1.0008 Cp, KJ/(KG)(K) 2.8230 2.5613 2.2704 GAMMAs 1.1984 1.2116 1.2339 SON VEL,M/SEC 1158.0 1108.6 954.7 MACH NUMBER 0.000 1.000 2.156 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2041 CSTAR, M/SEC 1628.2 1628.2 CF 0.6809 1.2641 Ivac, M/SEC 2023.5 2417.1 Isp, M/SEC 1108.6 2058.2 MOLE FRACTIONS *CO 0.32365 0.31960 0.29633 *CO2 0.07470 0.07968 0.10365 *H 0.00609 0.00284 0.00010 *H2 0.23860 0.24486 0.27012 H2O 0.35483 0.35230 0.32980 *O 0.00003 0.00001 0.00000 *OH 0.00207 0.00071 0.00001 *O2 0.00002 0.00000 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.10000 %FUEL= 47.619047 R,EQ.RATIO= 1.679718 PHI,EQ.RATIO= 1.894319 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7914 10.000 P, BAR 8.9632 5.0036 0.89632 T, K 2592.92 2325.71 1665.56 RHO, KG/CU M 8.0111-1 4.9859-1 1.2472-1 H, KJ/KG -3081.10 -3699.24 -5169.05 U, KJ/KG -4199.94 -4702.77 -5887.74 G, KJ/KG -36904.3 -34036.8 -26895.4 S, KJ/(KG)(K) 13.0445 13.0445 13.0445 M, (1/n) 19.269 19.269 19.269 Cp, KJ/(KG)(K) 2.3329 2.2923 2.1485 GAMMAs 1.2269 1.2319 1.2513 SON VEL,M/SEC 1171.6 1111.9 948.3 MACH NUMBER 0.000 1.000 2.155 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1752 CSTAR, M/SEC 1616.8 1616.8 CF 0.6877 1.2639 Ivac, M/SEC 2014.4 2395.2 Isp, M/SEC 1111.9 2043.5 MOLE FRACTIONS *CO 0.32365 *CO2 0.07470 *H 0.00609 *H2 0.23860 H2O 0.35483 *O 0.00003 *OH 0.00207 *O2 0.00002 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.20000 %FUEL= 45.454544 R,EQ.RATIO= 1.571160 PHI,EQ.RATIO= 1.736459 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7651 10.000 P, BAR 8.9632 5.0781 0.89632 T, K 2792.12 2571.14 1919.23 RHO, KG/CU M 7.7511-1 4.7910-1 1.1383-1 H, KJ/KG -2959.49 -3589.01 -5184.76 U, KJ/KG -4115.86 -4648.94 -5972.20 G, KJ/KG -38935.7 -36718.0 -29913.9 S, KJ/(KG)(K) 12.8849 12.8849 12.8849 M, (1/n) 20.076 20.169 20.265 (dLV/dLP)t -1.00501 -1.00255 -1.00013 (dLV/dLT)p 1.1083 1.0590 1.0038 Cp, KJ/(KG)(K) 3.3125 2.8766 2.2796 GAMMAs 1.1745 1.1879 1.2213 SON VEL,M/SEC 1165.4 1122.1 980.7 MACH NUMBER 0.000 1.000 2.151 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2387 CSTAR, M/SEC 1667.3 1667.3 CF 0.6730 1.2653 Ivac, M/SEC 2066.7 2482.9 Isp, M/SEC 1122.1 2109.6 MOLE FRACTIONS *CO 0.30737 0.30456 0.28630 *CO2 0.08878 0.09344 0.11359 *H 0.01175 0.00678 0.00046 *H2 0.19472 0.20010 0.22231 H2O 0.39036 0.39203 0.37727 *O 0.00025 0.00007 0.00000 *OH 0.00655 0.00297 0.00007 *O2 0.00020 0.00005 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.20000 %FUEL= 45.454544 R,EQ.RATIO= 1.571160 PHI,EQ.RATIO= 1.736459 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7856 10.000 P, BAR 8.9632 5.0196 0.89632 T, K 2792.12 2514.56 1821.18 RHO, KG/CU M 7.7511-1 4.8200-1 1.1883-1 H, KJ/KG -2959.49 -3596.10 -5132.06 U, KJ/KG -4115.86 -4637.51 -5886.32 G, KJ/KG -38935.7 -35996.0 -28597.9 S, KJ/(KG)(K) 12.8849 12.8849 12.8849 M, (1/n) 20.076 20.076 20.076 Cp, KJ/(KG)(K) 2.3110 2.2749 2.1438 GAMMAs 1.2183 1.2226 1.2394 SON VEL,M/SEC 1186.9 1128.4 966.9 MACH NUMBER 0.000 1.000 2.156 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1956 CSTAR, M/SEC 1648.0 1648.0 CF 0.6847 1.2649 Ivac, M/SEC 2051.3 2446.3 Isp, M/SEC 1128.4 2084.5 MOLE FRACTIONS *CO 0.30737 *CO2 0.08878 *H 0.01175 *H2 0.19472 H2O 0.39036 *O 0.00025 *OH 0.00655 *O2 0.00020 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.30000 %FUEL= 43.478262 R,EQ.RATIO= 1.475781 PHI,EQ.RATIO= 1.602885 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7503 10.000 P, BAR 8.9632 5.1209 0.89632 T, K 2943.35 2746.27 2112.66 RHO, KG/CU M 7.6204-1 4.7003-1 1.0803-1 H, KJ/KG -2848.45 -3482.53 -5152.03 U, KJ/KG -4024.67 -4572.01 -5981.73 G, KJ/KG -40288.8 -38415.9 -32025.7 S, KJ/(KG)(K) 12.7203 12.7203 12.7203 M, (1/n) 20.806 20.959 21.171 (dLV/dLP)t -1.01002 -1.00589 -1.00049 (dLV/dLT)p 1.2103 1.1312 1.0133 Cp, KJ/(KG)(K) 4.0857 3.4583 2.3588 GAMMAs 1.1537 1.1640 1.2055 SON VEL,M/SEC 1164.9 1126.1 1000.1 MACH NUMBER 0.000 1.000 2.146 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2827 CSTAR, M/SEC 1693.4 1693.4 CF 0.6650 1.2676 Ivac, M/SEC 2093.6 2533.0 Isp, M/SEC 1126.1 2146.4 MOLE FRACTIONS *CO 0.28790 0.28545 0.27158 *CO2 0.10482 0.11015 0.12803 *H 0.01753 0.01196 0.00151 *H2 0.15697 0.16039 0.17880 H2O 0.41599 0.42281 0.41965 *O 0.00101 0.00040 0.00000 *OH 0.01471 0.00841 0.00043 *O2 0.00106 0.00042 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.30000 %FUEL= 43.478262 R,EQ.RATIO= 1.475781 PHI,EQ.RATIO= 1.602885 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7814 10.000 P, BAR 8.9632 5.0315 0.89632 T, K 2943.35 2658.71 1941.81 RHO, KG/CU M 7.6204-1 4.7357-1 1.1551-1 H, KJ/KG -2848.45 -3494.29 -5069.45 U, KJ/KG -4024.67 -4556.75 -5845.43 G, KJ/KG -40288.8 -37313.9 -29769.9 S, KJ/(KG)(K) 12.7203 12.7203 12.7203 M, (1/n) 20.806 20.806 20.806 Cp, KJ/(KG)(K) 2.2848 2.2520 2.1314 GAMMAs 1.2120 1.2157 1.2308 SON VEL,M/SEC 1194.0 1136.5 977.3 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2109 CSTAR, M/SEC 1665.3 1665.3 CF 0.6825 1.2656 Ivac, M/SEC 2071.4 2475.8 Isp, M/SEC 1136.5 2107.6 MOLE FRACTIONS *CO 0.28790 *CO2 0.10482 *H 0.01753 *H2 0.15697 H2O 0.41599 *O 0.00101 *OH 0.01471 *O2 0.00106 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.40000 %FUEL= 41.666667 R,EQ.RATIO= 1.391320 PHI,EQ.RATIO= 1.488393 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7376 10.000 P, BAR 8.9632 5.1583 0.89632 T, K 3048.88 2875.79 2293.39 RHO, KG/CU M 7.5849-1 4.6732-1 1.0364-1 H, KJ/KG -2746.67 -3377.93 -5099.87 U, KJ/KG -3928.38 -4481.74 -5964.68 G, KJ/KG -41028.4 -39486.3 -33895.7 S, KJ/(KG)(K) 12.5560 12.5560 12.5560 M, (1/n) 21.452 21.662 22.049 (dLV/dLP)t -1.01728 -1.01163 -1.00149 (dLV/dLT)p 1.3548 1.2525 1.0388 Cp, KJ/(KG)(K) 5.1223 4.3838 2.5840 GAMMAs 1.1384 1.1438 1.1848 SON VEL,M/SEC 1159.9 1123.6 1012.2 MACH NUMBER 0.000 1.000 2.143 PERFORMANCE PARAMETERS Ae/At 1.0000 2.3353 CSTAR, M/SEC 1707.0 1707.0 CF 0.6582 1.2709 Ivac, M/SEC 2106.0 2568.1 Isp, M/SEC 1123.6 2169.4 MOLE FRACTIONS *CO 0.26686 0.26363 0.25188 *CO2 0.12117 0.12820 0.14697 *H 0.02181 0.01672 0.00370 HO2 0.00001 0.00000 0.00000 *H2 0.12680 0.12773 0.13998 H2O 0.43159 0.44298 0.45547 *O 0.00267 0.00141 0.00003 *OH 0.02551 0.01736 0.00192 *O2 0.00358 0.00195 0.00005 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.40000 %FUEL= 41.666667 R,EQ.RATIO= 1.391320 PHI,EQ.RATIO= 1.488393 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7785 10.000 P, BAR 8.9632 5.0398 0.89632 T, K 3048.88 2759.86 2027.74 RHO, KG/CU M 7.5849-1 4.7115-1 1.1405-1 H, KJ/KG -2746.67 -3394.32 -4986.04 U, KJ/KG -3928.38 -4464.01 -5771.97 G, KJ/KG -41028.4 -38047.1 -30446.4 S, KJ/(KG)(K) 12.5560 12.5560 12.5560 M, (1/n) 21.452 21.452 21.452 Cp, KJ/(KG)(K) 2.2555 2.2252 2.1126 GAMMAs 1.2075 1.2109 1.2247 SON VEL,M/SEC 1194.5 1138.1 981.1 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2217 CSTAR, M/SEC 1671.5 1671.5 CF 0.6809 1.2661 Ivac, M/SEC 2078.0 2487.7 Isp, M/SEC 1138.1 2116.3 MOLE FRACTIONS *CO 0.26686 *CO2 0.12117 *H 0.02181 HO2 0.00001 *H2 0.12680 H2O 0.43159 *O 0.00267 *OH 0.02551 *O2 0.00358 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.50000 %FUEL= 40.000000 R,EQ.RATIO= 1.316004 PHI,EQ.RATIO= 1.389167 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7289 10.000 P, BAR 8.9632 5.1844 0.89632 T, K 3117.30 2961.97 2449.35 RHO, KG/CU M 7.6143-1 4.6889-1 1.0064-1 H, KJ/KG -2653.03 -3277.73 -5028.37 U, KJ/KG -3830.18 -4383.40 -5918.94 G, KJ/KG -41293.3 -39992.6 -35389.0 S, KJ/(KG)(K) 12.3954 12.3954 12.3954 M, (1/n) 22.018 22.274 22.867 (dLV/dLP)t -1.02566 -1.01949 -1.00398 (dLV/dLT)p 1.5185 1.4150 1.1009 Cp, KJ/(KG)(K) 6.2293 5.5556 3.1209 GAMMAs 1.1288 1.1300 1.1590 SON VEL,M/SEC 1152.7 1117.8 1016.0 MACH NUMBER 0.000 1.000 2.145 PERFORMANCE PARAMETERS Ae/At 1.0000 2.3892 CSTAR, M/SEC 1710.2 1710.2 CF 0.6536 1.2745 Ivac, M/SEC 2106.9 2588.2 Isp, M/SEC 1117.8 2179.6 MOLE FRACTIONS *CO 0.24603 0.24132 0.22754 *CO2 0.13631 0.14546 0.16956 *H 0.02409 0.01979 0.00693 HO2 0.00002 0.00001 0.00000 *H2 0.10390 0.10280 0.10700 H2O 0.43918 0.45345 0.48214 *O 0.00514 0.00332 0.00026 *OH 0.03678 0.02805 0.00608 *O2 0.00854 0.00580 0.00048 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.50000 %FUEL= 40.000000 R,EQ.RATIO= 1.316004 PHI,EQ.RATIO= 1.389167 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7764 10.000 P, BAR 8.9632 5.0456 0.89632 T, K 3117.30 2825.88 2084.73 RHO, KG/CU M 7.6143-1 4.7283-1 1.1386-1 H, KJ/KG -2653.03 -3297.37 -4889.25 U, KJ/KG -3830.18 -4364.47 -5676.49 G, KJ/KG -41293.3 -38325.3 -30730.4 S, KJ/(KG)(K) 12.3954 12.3954 12.3954 M, (1/n) 22.018 22.018 22.018 Cp, KJ/(KG)(K) 2.2249 2.1962 2.0896 GAMMAs 1.2044 1.2076 1.2206 SON VEL,M/SEC 1190.7 1135.2 980.2 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2292 CSTAR, M/SEC 1669.9 1669.9 CF 0.6798 1.2664 Ivac, M/SEC 2075.2 2487.1 Isp, M/SEC 1135.2 2114.8 MOLE FRACTIONS *CO 0.24603 *CO2 0.13631 *H 0.02409 HO2 0.00002 *H2 0.10390 H2O 0.43918 *O 0.00514 *OH 0.03678 *O2 0.00854 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.60000 %FUEL= 38.461538 R,EQ.RATIO= 1.248422 PHI,EQ.RATIO= 1.302344 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7238 10.000 P, BAR 8.9632 5.1997 0.89632 T, K 3159.51 3015.04 2564.30 RHO, KG/CU M 7.6834-1 4.7303-1 9.9142-2 H, KJ/KG -2566.59 -3183.26 -4940.87 U, KJ/KG -3733.14 -4282.49 -5844.94 G, KJ/KG -41240.8 -40089.0 -36329.3 S, KJ/(KG)(K) 12.2406 12.2406 12.2406 M, (1/n) 22.519 22.806 23.583 (dLV/dLP)t -1.03335 -1.02765 -1.00933 (dLV/dLT)p 1.6670 1.5808 1.2308 Cp, KJ/(KG)(K) 7.1696 6.6796 4.1903 GAMMAs 1.1233 1.1220 1.1339 SON VEL,M/SEC 1144.7 1110.6 1012.5 MACH NUMBER 0.000 1.000 2.152 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4316 CSTAR, M/SEC 1706.2 1706.2 CF 0.6509 1.2772 Ivac, M/SEC 2100.4 2594.0 Isp, M/SEC 1110.6 2179.1 MOLE FRACTIONS *CO 0.22645 0.22023 0.20102 *CO2 0.14955 0.16056 0.19275 *H 0.02478 0.02110 0.01000 HO2 0.00003 0.00002 0.00000 *H2 0.08671 0.08441 0.08147 H2O 0.44143 0.45709 0.49741 *O 0.00805 0.00584 0.00108 *OH 0.04693 0.03827 0.01356 *O2 0.01606 0.01249 0.00269 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.60000 %FUEL= 38.461538 R,EQ.RATIO= 1.248422 PHI,EQ.RATIO= 1.302344 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7751 10.000 P, BAR 8.9632 5.0494 0.89632 T, K 3159.51 2866.96 2120.91 RHO, KG/CU M 7.6834-1 4.7702-1 1.1446-1 H, KJ/KG -2566.59 -3204.58 -4786.38 U, KJ/KG -3733.14 -4263.11 -5569.47 G, KJ/KG -41240.8 -38297.7 -30747.5 S, KJ/(KG)(K) 12.2406 12.2406 12.2406 M, (1/n) 22.519 22.519 22.519 Cp, KJ/(KG)(K) 2.1940 2.1666 2.0643 GAMMAs 1.2023 1.2054 1.2178 SON VEL,M/SEC 1184.3 1129.6 976.5 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2343 CSTAR, M/SEC 1663.4 1663.4 CF 0.6791 1.2667 Ivac, M/SEC 2066.7 2478.7 Isp, M/SEC 1129.6 2107.0 MOLE FRACTIONS *CO 0.22645 *CO2 0.14955 *H 0.02478 HO2 0.00003 *H2 0.08671 H2O 0.44143 *O 0.00805 *OH 0.04693 *O2 0.01606 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.70000 %FUEL= 37.037036 R,EQ.RATIO= 1.187443 PHI,EQ.RATIO= 1.225736 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7210 10.000 P, BAR 8.9632 5.2080 0.89632 T, K 3184.45 3046.15 2634.20 RHO, KG/CU M 7.7756-1 4.7862-1 9.8948-2 H, KJ/KG -2486.55 -3094.63 -4844.04 U, KJ/KG -3639.28 -4182.77 -5749.88 G, KJ/KG -40994.1 -39929.8 -36697.6 S, KJ/(KG)(K) 12.0923 12.0923 12.0923 M, (1/n) 22.969 23.276 24.179 (dLV/dLP)t -1.03925 -1.03432 -1.01707 (dLV/dLT)p 1.7802 1.7151 1.4140 Cp, KJ/(KG)(K) 7.8307 7.5272 5.6143 GAMMAs 1.1201 1.1177 1.1178 SON VEL,M/SEC 1136.3 1102.8 1006.3 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4566 CSTAR, M/SEC 1698.1 1698.1 CF 0.6494 1.2787 Ivac, M/SEC 2089.5 2588.6 Isp, M/SEC 1102.8 2171.4 MOLE FRACTIONS *CO 0.20848 0.20101 0.17608 *CO2 0.16083 0.17323 0.21269 *H 0.02445 0.02119 0.01174 HO2 0.00004 0.00003 0.00000 *H2 0.07362 0.07073 0.06352 H2O 0.44042 0.45658 0.50265 *O 0.01101 0.00855 0.00264 *OH 0.05536 0.04692 0.02221 *O2 0.02576 0.02176 0.00847 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.70000 %FUEL= 37.037036 R,EQ.RATIO= 1.187443 PHI,EQ.RATIO= 1.225736 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7741 10.000 P, BAR 8.9632 5.0521 0.89632 T, K 3184.45 2891.54 2143.17 RHO, KG/CU M 7.7756-1 4.8267-1 1.1553-1 H, KJ/KG -2486.55 -3116.61 -4682.57 U, KJ/KG -3639.28 -4163.31 -5458.37 G, KJ/KG -40994.1 -38082.1 -30598.5 S, KJ/(KG)(K) 12.0923 12.0923 12.0923 M, (1/n) 22.969 22.969 22.969 Cp, KJ/(KG)(K) 2.1639 2.1373 2.0384 GAMMAs 1.2009 1.2039 1.2159 SON VEL,M/SEC 1176.6 1122.5 971.2 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2377 CSTAR, M/SEC 1654.3 1654.3 CF 0.6786 1.2669 Ivac, M/SEC 2055.0 2465.9 Isp, M/SEC 1122.5 2095.7 MOLE FRACTIONS *CO 0.20848 *CO2 0.16083 *H 0.02445 HO2 0.00004 *H2 0.07362 H2O 0.44042 *O 0.01101 *OH 0.05536 *O2 0.02576 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.80000 %FUEL= 35.714286 R,EQ.RATIO= 1.132144 PHI,EQ.RATIO= 1.157639 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7195 10.000 P, BAR 8.9632 5.2126 0.89632 T, K 3198.11 3063.30 2671.63 RHO, KG/CU M 7.8806-1 4.8502-1 9.9573-2 H, KJ/KG -2412.23 -3011.53 -4744.29 U, KJ/KG -3549.60 -4086.23 -5644.45 G, KJ/KG -40633.2 -39621.3 -36673.2 S, KJ/(KG)(K) 11.9511 11.9511 11.9511 M, (1/n) 23.379 23.699 24.677 (dLV/dLP)t -1.04318 -1.03889 -1.02412 (dLV/dLT)p 1.8560 1.8070 1.5784 Cp, KJ/(KG)(K) 8.2230 8.0527 6.8122 GAMMAs 1.1183 1.1153 1.1100 SON VEL,M/SEC 1127.8 1094.8 999.6 MACH NUMBER 0.000 1.000 2.161 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4693 CSTAR, M/SEC 1688.0 1688.0 CF 0.6486 1.2795 Ivac, M/SEC 2076.4 2576.5 Isp, M/SEC 1094.8 2159.7 MOLE FRACTIONS *CO 0.19212 0.18370 0.15446 *CO2 0.17036 0.18374 0.22814 *H 0.02355 0.02057 0.01220 HO2 0.00006 0.00004 0.00001 *H2 0.06342 0.06028 0.05111 H2O 0.43747 0.45369 0.50184 H2O2 0.00001 0.00000 0.00000 *O 0.01379 0.01114 0.00453 *OH 0.06206 0.05379 0.02972 *O2 0.03716 0.03303 0.01799 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.80000 %FUEL= 35.714286 R,EQ.RATIO= 1.132144 PHI,EQ.RATIO= 1.157639 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7735 10.000 P, BAR 8.9632 5.0540 0.89632 T, K 3198.11 2905.31 2156.21 RHO, KG/CU M 7.8806-1 4.8914-1 1.1689-1 H, KJ/KG -2412.23 -3033.64 -4580.72 U, KJ/KG -3549.60 -4066.88 -5347.55 G, KJ/KG -40633.2 -37755.3 -30349.9 S, KJ/(KG)(K) 11.9511 11.9511 11.9511 M, (1/n) 23.379 23.379 23.379 Cp, KJ/(KG)(K) 2.1348 2.1089 2.0127 GAMMAs 1.1999 1.2028 1.2146 SON VEL,M/SEC 1168.2 1114.8 965.1 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2402 CSTAR, M/SEC 1643.7 1643.7 CF 0.6782 1.2670 Ivac, M/SEC 2041.6 2450.8 Isp, M/SEC 1114.8 2082.5 MOLE FRACTIONS *CO 0.19212 *CO2 0.17036 *H 0.02355 HO2 0.00006 *H2 0.06342 H2O 0.43747 H2O2 0.00001 *O 0.01379 *OH 0.06206 *O2 0.03716 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.90000 %FUEL= 34.482759 R,EQ.RATIO= 1.081765 PHI,EQ.RATIO= 1.096711 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7187 10.000 P, BAR 8.9632 5.2151 0.89632 T, K 3204.24 3071.41 2689.81 RHO, KG/CU M 7.9927-1 4.9188-1 1.0063-1 H, KJ/KG -2343.04 -2933.57 -4645.54 U, KJ/KG -3464.45 -3993.80 -5536.27 G, KJ/KG -40206.9 -39227.8 -36430.5 S, KJ/(KG)(K) 11.8168 11.8168 11.8168 M, (1/n) 23.757 24.086 25.108 (dLV/dLP)t -1.04545 -1.04156 -1.02865 (dLV/dLT)p 1.9005 1.8612 1.6835 Cp, KJ/(KG)(K) 8.4055 8.3126 7.5135 GAMMAs 1.1172 1.1140 1.1065 SON VEL,M/SEC 1119.3 1086.8 992.8 MACH NUMBER 0.000 1.000 2.162 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4755 CSTAR, M/SEC 1676.7 1676.7 CF 0.6481 1.2798 Ivac, M/SEC 2062.4 2561.0 Isp, M/SEC 1086.8 2145.9 MOLE FRACTIONS *CO 0.17723 0.16812 0.13601 *CO2 0.17841 0.19245 0.23986 *H 0.02235 0.01958 0.01188 HO2 0.00007 0.00005 0.00001 *H2 0.05526 0.05207 0.04219 H2O 0.43337 0.44945 0.49796 H2O2 0.00001 0.00000 0.00000 *O 0.01626 0.01346 0.00636 *OH 0.06724 0.05906 0.03544 *O2 0.04980 0.04576 0.03030 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.90000 %FUEL= 34.482759 R,EQ.RATIO= 1.081765 PHI,EQ.RATIO= 1.096711 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7730 10.000 P, BAR 8.9632 5.0552 0.89632 T, K 3204.24 2911.84 2163.04 RHO, KG/CU M 7.9927-1 4.9606-1 1.1840-1 H, KJ/KG -2343.04 -2955.56 -4482.32 U, KJ/KG -3464.45 -3974.64 -5239.34 G, KJ/KG -40206.9 -37364.2 -30042.6 S, KJ/(KG)(K) 11.8168 11.8168 11.8168 M, (1/n) 23.757 23.757 23.757 Cp, KJ/(KG)(K) 2.1071 2.0817 1.9876 GAMMAs 1.1992 1.2021 1.2137 SON VEL,M/SEC 1159.6 1106.8 958.5 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2418 CSTAR, M/SEC 1632.5 1632.5 CF 0.6780 1.2671 Ivac, M/SEC 2027.5 2434.4 Isp, M/SEC 1106.8 2068.5 MOLE FRACTIONS *CO 0.17723 *CO2 0.17841 *H 0.02235 HO2 0.00007 *H2 0.05526 H2O 0.43337 H2O2 0.00001 *O 0.01626 *OH 0.06724 *O2 0.04980 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.00000 %FUEL= 33.333333 R,EQ.RATIO= 1.035680 PHI,EQ.RATIO= 1.041875 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7182 10.000 P, BAR 8.9632 5.2165 0.89632 T, K 3205.20 3073.48 2696.65 RHO, KG/CU M 8.1085-1 4.9898-1 1.0191-1 H, KJ/KG -2278.46 -2860.36 -4549.71 U, KJ/KG -3383.86 -3905.79 -5429.25 G, KJ/KG -39744.6 -38786.8 -36071.4 S, KJ/(KG)(K) 11.6892 11.6892 11.6892 M, (1/n) 24.108 24.444 25.492 (dLV/dLP)t -1.04646 -1.04277 -1.03077 (dLV/dLT)p 1.9216 1.8870 1.7333 Cp, KJ/(KG)(K) 8.4395 8.3825 7.7876 GAMMAs 1.1166 1.1132 1.1050 SON VEL,M/SEC 1111.0 1078.8 985.9 MACH NUMBER 0.000 1.000 2.162 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4784 CSTAR, M/SEC 1665.1 1665.1 CF 0.6479 1.2800 Ivac, M/SEC 2047.9 2544.0 Isp, M/SEC 1078.8 2131.3 MOLE FRACTIONS *CO 0.16367 0.15405 0.12012 *CO2 0.18520 0.19968 0.24878 *H 0.02102 0.01840 0.01118 HO2 0.00009 0.00006 0.00002 *H2 0.04860 0.04545 0.03544 H2O 0.42858 0.44442 0.49255 H2O2 0.00001 0.00000 0.00000 *O 0.01838 0.01546 0.00793 *OH 0.07113 0.06298 0.03951 *O2 0.06332 0.05950 0.04448 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.00000 %FUEL= 33.333333 R,EQ.RATIO= 1.035680 PHI,EQ.RATIO= 1.041875 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7727 10.000 P, BAR 8.9632 5.0561 0.89632 T, K 3205.20 2913.37 2165.55 RHO, KG/CU M 8.1085-1 5.0322-1 1.2001-1 H, KJ/KG -2278.46 -2882.11 -4388.00 U, KJ/KG -3383.86 -3886.87 -5134.86 G, KJ/KG -39744.6 -36937.1 -29701.5 S, KJ/(KG)(K) 11.6892 11.6892 11.6892 M, (1/n) 24.108 24.108 24.108 Cp, KJ/(KG)(K) 2.0807 2.0557 1.9633 GAMMAs 1.1987 1.2016 1.2131 SON VEL,M/SEC 1151.1 1098.8 951.8 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2430 CSTAR, M/SEC 1621.0 1621.0 CF 0.6778 1.2671 Ivac, M/SEC 2013.2 2417.6 Isp, M/SEC 1098.8 2054.0 MOLE FRACTIONS *CO 0.16367 *CO2 0.18520 *H 0.02102 HO2 0.00009 *H2 0.04860 H2O 0.42858 H2O2 0.00001 *O 0.01838 *OH 0.07113 *O2 0.06332 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.10000 %FUEL= 32.258066 R,EQ.RATIO= 0.993360 PHI,EQ.RATIO= 0.992262 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7180 10.000 P, BAR 8.9632 5.2171 0.89632 T, K 3202.47 3071.35 2696.41 RHO, KG/CU M 8.2260-1 5.0619-1 1.0331-1 H, KJ/KG -2218.04 -2791.55 -4457.59 U, KJ/KG -3307.66 -3822.22 -5325.20 G, KJ/KG -39264.1 -38320.8 -35649.5 S, KJ/(KG)(K) 11.5680 11.5680 11.5680 M, (1/n) 24.437 24.777 25.840 (dLV/dLP)t -1.04658 -1.04295 -1.03119 (dLV/dLT)p 1.9259 1.8926 1.7444 Cp, KJ/(KG)(K) 8.3731 8.3251 7.7792 GAMMAs 1.1163 1.1129 1.1046 SON VEL,M/SEC 1102.9 1071.0 978.9 MACH NUMBER 0.000 1.000 2.162 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4795 CSTAR, M/SEC 1653.4 1653.4 CF 0.6478 1.2801 Ivac, M/SEC 2033.3 2526.3 Isp, M/SEC 1071.0 2116.4 MOLE FRACTIONS *CO 0.15127 0.14130 0.10627 *CO2 0.19095 0.20568 0.25560 *H 0.01964 0.01715 0.01030 HO2 0.00010 0.00007 0.00002 *H2 0.04307 0.03999 0.03014 H2O 0.42340 0.43897 0.48638 H2O2 0.00001 0.00001 0.00000 *O 0.02016 0.01711 0.00918 *OH 0.07396 0.06579 0.04226 *O2 0.07743 0.07394 0.05984 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.10000 %FUEL= 32.258066 R,EQ.RATIO= 0.993360 PHI,EQ.RATIO= 0.992262 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7725 10.000 P, BAR 8.9632 5.0567 0.89632 T, K 3202.47 2911.35 2164.95 RHO, KG/CU M 8.2260-1 5.1049-1 1.2168-1 H, KJ/KG -2218.04 -2813.00 -4298.00 U, KJ/KG -3307.66 -3803.56 -5034.61 G, KJ/KG -39264.1 -36491.3 -29342.1 S, KJ/(KG)(K) 11.5680 11.5680 11.5680 M, (1/n) 24.437 24.437 24.437 Cp, KJ/(KG)(K) 2.0556 2.0309 1.9400 GAMMAs 1.1984 1.2012 1.2127 SON VEL,M/SEC 1142.7 1090.8 945.1 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2438 CSTAR, M/SEC 1609.6 1609.6 CF 0.6777 1.2671 Ivac, M/SEC 1998.9 2400.7 Isp, M/SEC 1090.8 2039.6 MOLE FRACTIONS *CO 0.15127 *CO2 0.19095 *H 0.01964 HO2 0.00010 *H2 0.04307 H2O 0.42340 H2O2 0.00001 *O 0.02016 *OH 0.07396 *O2 0.07743 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.20000 %FUEL= 31.250000 R,EQ.RATIO= 0.954364 PHI,EQ.RATIO= 0.947159 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7180 10.000 P, BAR 8.9632 5.2173 0.89632 T, K 3197.06 3066.20 2691.43 RHO, KG/CU M 8.3439-1 5.1343-1 1.0478-1 H, KJ/KG -2161.40 -2726.78 -4369.48 U, KJ/KG -3235.62 -3742.94 -5224.90 G, KJ/KG -38776.6 -37843.2 -35193.7 S, KJ/(KG)(K) 11.4527 11.4527 11.4527 M, (1/n) 24.746 25.088 26.160 (dLV/dLP)t -1.04606 -1.04241 -1.03053 (dLV/dLT)p 1.9186 1.8843 1.7310 Cp, KJ/(KG)(K) 8.2406 8.1852 7.6024 GAMMAs 1.1161 1.1128 1.1047 SON VEL,M/SEC 1095.0 1063.4 972.1 MACH NUMBER 0.000 1.000 2.162 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4795 CSTAR, M/SEC 1641.7 1641.7 CF 0.6477 1.2801 Ivac, M/SEC 2019.0 2508.5 Isp, M/SEC 1063.4 2101.5 MOLE FRACTIONS *CO 0.13991 0.12970 0.09410 *CO2 0.19580 0.21066 0.26080 *H 0.01828 0.01590 0.00936 HO2 0.00011 0.00008 0.00002 *H2 0.03840 0.03542 0.02585 H2O 0.41799 0.43328 0.47983 H2O2 0.00001 0.00001 0.00000 *O 0.02162 0.01844 0.01013 *OH 0.07593 0.06770 0.04396 *O2 0.09194 0.08881 0.07594 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.20000 %FUEL= 31.250000 R,EQ.RATIO= 0.954364 PHI,EQ.RATIO= 0.947159 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7724 10.000 P, BAR 8.9632 5.0571 0.89632 T, K 3197.06 2906.71 2162.07 RHO, KG/CU M 8.3439-1 5.1780-1 1.2338-1 H, KJ/KG -2161.40 -2747.90 -4212.29 U, KJ/KG -3235.62 -3724.55 -4938.74 G, KJ/KG -38776.6 -36037.7 -28973.9 S, KJ/(KG)(K) 11.4527 11.4527 11.4527 M, (1/n) 24.746 24.746 24.746 Cp, KJ/(KG)(K) 2.0318 2.0074 1.9177 GAMMAs 1.1981 1.2010 1.2124 SON VEL,M/SEC 1134.5 1083.0 938.5 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2442 CSTAR, M/SEC 1598.3 1598.3 CF 0.6776 1.2672 Ivac, M/SEC 1984.8 2384.0 Isp, M/SEC 1083.0 2025.3 MOLE FRACTIONS *CO 0.13991 *CO2 0.19580 *H 0.01828 HO2 0.00011 *H2 0.03840 H2O 0.41799 H2O2 0.00001 *O 0.02162 *OH 0.07593 *O2 0.09194 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.30000 %FUEL= 30.303031 R,EQ.RATIO= 0.918313 PHI,EQ.RATIO= 0.905979 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7180 10.000 P, BAR 8.9632 5.2172 0.89632 T, K 3189.65 3058.81 2683.10 RHO, KG/CU M 8.4616-1 5.2067-1 1.0629-1 H, KJ/KG -2108.20 -2665.73 -4285.36 U, KJ/KG -3167.46 -3667.75 -5128.61 G, KJ/KG -38288.9 -37362.4 -34720.2 S, KJ/(KG)(K) 11.3432 11.3432 11.3432 M, (1/n) 25.036 25.381 26.456 (dLV/dLP)t -1.04512 -1.04140 -1.02923 (dLV/dLT)p 1.9031 1.8666 1.7031 Cp, KJ/(KG)(K) 8.0656 7.9933 7.3311 GAMMAs 1.1161 1.1128 1.1051 SON VEL,M/SEC 1087.3 1056.0 965.3 MACH NUMBER 0.000 1.000 2.162 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4788 CSTAR, M/SEC 1630.2 1630.2 CF 0.6477 1.2800 Ivac, M/SEC 2004.9 2490.8 Isp, M/SEC 1056.0 2086.7 MOLE FRACTIONS *CO 0.12948 0.11911 0.08332 *CO2 0.19988 0.21479 0.26471 *H 0.01696 0.01468 0.00842 HO2 0.00012 0.00009 0.00003 *H2 0.03442 0.03154 0.02231 H2O 0.41249 0.42748 0.47311 H2O2 0.00001 0.00001 0.00000 *O 0.02277 0.01947 0.01079 *OH 0.07719 0.06888 0.04483 *O2 0.10668 0.10395 0.09248 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.30000 %FUEL= 30.303031 R,EQ.RATIO= 0.918313 PHI,EQ.RATIO= 0.905979 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7723 10.000 P, BAR 8.9632 5.0573 0.89632 T, K 3189.65 2900.12 2157.45 RHO, KG/CU M 8.4616-1 5.2510-1 1.2510-1 H, KJ/KG -2108.20 -2686.51 -4130.72 U, KJ/KG -3167.46 -3649.63 -4847.20 G, KJ/KG -38288.9 -35583.1 -28603.0 S, KJ/(KG)(K) 11.3432 11.3432 11.3432 M, (1/n) 25.036 25.036 25.036 Cp, KJ/(KG)(K) 2.0092 1.9850 1.8964 GAMMAs 1.1980 1.2009 1.2123 SON VEL,M/SEC 1126.5 1075.5 932.0 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2445 CSTAR, M/SEC 1587.2 1587.2 CF 0.6776 1.2672 Ivac, M/SEC 1971.0 2367.5 Isp, M/SEC 1075.5 2011.2 MOLE FRACTIONS *CO 0.12948 *CO2 0.19988 *H 0.01696 HO2 0.00012 *H2 0.03442 H2O 0.41249 H2O2 0.00001 *O 0.02277 *OH 0.07719 *O2 0.10668 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.40000 %FUEL= 29.411764 R,EQ.RATIO= 0.884887 PHI,EQ.RATIO= 0.868229 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7181 10.000 P, BAR 8.9632 5.2169 0.89632 T, K 3180.69 3049.70 2672.27 RHO, KG/CU M 8.5787-1 5.2787-1 1.0783-1 H, KJ/KG -2058.12 -2608.10 -4205.13 U, KJ/KG -3102.94 -3596.39 -5036.33 G, KJ/KG -37805.6 -36883.4 -34238.5 S, KJ/(KG)(K) 11.2389 11.2389 11.2389 M, (1/n) 25.311 25.657 26.731 (dLV/dLP)t -1.04388 -1.04008 -1.02756 (dLV/dLT)p 1.8820 1.8426 1.6668 Cp, KJ/(KG)(K) 7.8639 7.7696 7.0099 GAMMAs 1.1162 1.1130 1.1058 SON VEL,M/SEC 1079.9 1048.8 958.7 MACH NUMBER 0.000 1.000 2.161 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4776 CSTAR, M/SEC 1619.0 1619.0 CF 0.6478 1.2799 Ivac, M/SEC 1991.1 2473.3 Isp, M/SEC 1048.8 2072.2 MOLE FRACTIONS *CO 0.11988 0.10943 0.07373 *CO2 0.20331 0.21818 0.26758 *H 0.01570 0.01351 0.00752 HO2 0.00013 0.00009 0.00003 *H2 0.03097 0.02821 0.01933 H2O 0.40696 0.42166 0.46634 H2O2 0.00001 0.00001 0.00000 *O 0.02365 0.02023 0.01119 *OH 0.07786 0.06947 0.04506 *O2 0.12153 0.11922 0.10923 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.40000 %FUEL= 29.411764 R,EQ.RATIO= 0.884887 PHI,EQ.RATIO= 0.868229 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7723 10.000 P, BAR 8.9632 5.0574 0.89632 T, K 3180.69 2892.02 2151.48 RHO, KG/CU M 8.5787-1 5.3236-1 1.2682-1 H, KJ/KG -2058.12 -2628.54 -4053.10 U, KJ/KG -3102.94 -3578.53 -4759.84 G, KJ/KG -37805.6 -35131.7 -28233.4 S, KJ/(KG)(K) 11.2389 11.2389 11.2389 M, (1/n) 25.311 25.311 25.311 Cp, KJ/(KG)(K) 1.9877 1.9637 1.8760 GAMMAs 1.1980 1.2009 1.2123 SON VEL,M/SEC 1118.8 1068.1 925.6 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2445 CSTAR, M/SEC 1576.3 1576.3 CF 0.6776 1.2672 Ivac, M/SEC 1957.5 2351.3 Isp, M/SEC 1068.1 1997.5 MOLE FRACTIONS *CO 0.11988 *CO2 0.20331 *H 0.01570 HO2 0.00013 *H2 0.03097 H2O 0.40696 H2O2 0.00001 *O 0.02365 *OH 0.07786 *O2 0.12153 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.50000 %FUEL= 28.571429 R,EQ.RATIO= 0.853809 PHI,EQ.RATIO= 0.833500 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7183 10.000 P, BAR 8.9632 5.2163 0.89632 T, K 3170.52 3039.25 2659.48 RHO, KG/CU M 8.6947-1 5.3501-1 1.0939-1 H, KJ/KG -2010.91 -2553.62 -4128.58 U, KJ/KG -3041.78 -3528.62 -4947.95 G, KJ/KG -37329.2 -36409.6 -33754.2 S, KJ/(KG)(K) 11.1396 11.1396 11.1396 M, (1/n) 25.572 25.918 26.987 (dLV/dLP)t -1.04244 -1.03855 -1.02570 (dLV/dLT)p 1.8571 1.8145 1.6259 Cp, KJ/(KG)(K) 7.6464 7.5275 6.6659 GAMMAs 1.1163 1.1133 1.1068 SON VEL,M/SEC 1072.8 1041.8 952.3 MACH NUMBER 0.000 1.000 2.161 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4759 CSTAR, M/SEC 1608.0 1608.0 CF 0.6479 1.2798 Ivac, M/SEC 1977.7 2456.1 Isp, M/SEC 1041.8 2058.0 MOLE FRACTIONS *CO 0.11102 0.10054 0.06516 *CO2 0.20616 0.22094 0.26958 *H 0.01451 0.01241 0.00667 HO2 0.00014 0.00010 0.00003 *H2 0.02797 0.02531 0.01679 H2O 0.40145 0.41587 0.45959 H2O2 0.00001 0.00001 0.00000 *O 0.02428 0.02075 0.01137 *OH 0.07806 0.06956 0.04476 *O2 0.13640 0.13451 0.12605 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL C2H5OH(L) 1.0000000 -277526.833 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.50000 %FUEL= 28.571429 R,EQ.RATIO= 0.853809 PHI,EQ.RATIO= 0.833500 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7723 10.000 P, BAR 8.9632 5.0573 0.89632 T, K 3170.52 2882.73 2144.46 RHO, KG/CU M 8.6947-1 5.3956-1 1.2855-1 H, KJ/KG -2010.91 -2573.72 -3979.20 U, KJ/KG -3041.78 -3511.02 -4676.46 G, KJ/KG -37329.2 -34686.2 -27867.6 S, KJ/(KG)(K) 11.1396 11.1396 11.1396 M, (1/n) 25.572 25.572 25.572 Cp, KJ/(KG)(K) 1.9672 1.9434 1.8566 GAMMAs 1.1980 1.2009 1.2123 SON VEL,M/SEC 1111.3 1061.0 919.4 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2444 CSTAR, M/SEC 1565.8 1565.8 CF 0.6776 1.2672 Ivac, M/SEC 1944.4 2335.5 Isp, M/SEC 1061.0 1984.1 MOLE FRACTIONS *CO 0.11102 *CO2 0.20616 *H 0.01451 HO2 0.00014 *H2 0.02797 H2O 0.40145 H2O2 0.00001 *O 0.02428 *OH 0.07806 *O2 0.13640 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS #Compare to Kerosene (Jet-A): problem rocket case=1 p,psi=130, pi/p=10, eql, frozen, nfz=1, o/f=1.8 1.9 2.0 2.1 2.2 2.3 2.4 2.5 2.6, reactants fuel = Jet-A(L) , wt% 100, t(k) 298 oxid = O2(L) , wt% 100, t(k) 90 output siunits short end THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.80000 %FUEL= 35.714286 R,EQ.RATIO= 1.885930 PHI,EQ.RATIO= 1.885930 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7681 10.000 P, BAR 8.9632 5.0693 0.89632 T, K 2978.95 2743.66 2031.60 RHO, KG/CU M 7.0955-1 4.3883-1 1.0572-1 H, KJ/KG -908.63 -1597.62 -3327.35 U, KJ/KG -2171.84 -2752.79 -4175.19 G, KJ/KG -39255.1 -36915.4 -29479.2 S, KJ/(KG)(K) 12.8725 12.8725 12.8725 M, (1/n) 19.608 19.748 19.923 (dLV/dLP)t -1.00847 -1.00477 -1.00030 (dLV/dLT)p 1.1667 1.1008 1.0082 Cp, KJ/(KG)(K) 3.5850 3.0646 2.1906 GAMMAs 1.1800 1.1929 1.2397 SON VEL,M/SEC 1220.9 1173.9 1025.2 MACH NUMBER 0.000 1.000 2.145 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2155 CSTAR, M/SEC 1740.0 1740.0 CF 0.6747 1.2641 Ivac, M/SEC 2157.9 2584.9 Isp, M/SEC 1173.9 2199.4 MOLE FRACTIONS *CO 0.44678 0.44701 0.43646 *CO2 0.05545 0.05883 0.07387 *H 0.02442 0.01488 0.00111 HCO 0.00001 0.00000 0.00000 *H2 0.24336 0.25052 0.27224 H2O 0.22211 0.22502 0.21622 *O 0.00045 0.00013 0.00000 *OH 0.00726 0.00356 0.00009 *O2 0.00016 0.00005 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.80000 %FUEL= 35.714286 R,EQ.RATIO= 1.885930 PHI,EQ.RATIO= 1.885930 CHAMBER THROAT EXIT Pinf/P 1.0000 1.8010 10.000 P, BAR 8.9632 4.9767 0.89632 T, K 2978.95 2652.69 1870.93 RHO, KG/CU M 7.0955-1 4.4243-1 1.1298-1 H, KJ/KG -908.63 -1610.45 -3240.59 U, KJ/KG -2171.84 -2735.31 -4033.95 G, KJ/KG -39255.1 -35757.2 -27324.1 S, KJ/(KG)(K) 12.8725 12.8725 12.8725 M, (1/n) 19.608 19.608 19.608 Cp, KJ/(KG)(K) 2.1661 2.1351 2.0246 GAMMAs 1.2434 1.2478 1.2649 SON VEL,M/SEC 1253.3 1184.7 1001.8 MACH NUMBER 0.000 1.000 2.156 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1484 CSTAR, M/SEC 1710.0 1710.0 CF 0.6929 1.2630 Ivac, M/SEC 2134.2 2527.0 Isp, M/SEC 1184.7 2159.6 MOLE FRACTIONS *CO 0.44678 *CO2 0.05545 *H 0.02442 HCO 0.00001 *H2 0.24336 H2O 0.22211 *O 0.00045 *OH 0.00726 *O2 0.00016 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.90000 %FUEL= 34.482759 R,EQ.RATIO= 1.786671 PHI,EQ.RATIO= 1.786671 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7569 10.000 P, BAR 8.9632 5.1018 0.89632 T, K 3090.17 2873.34 2186.35 RHO, KG/CU M 7.0291-1 4.3418-1 1.0165-1 H, KJ/KG -891.29 -1581.51 -3366.68 U, KJ/KG -2166.44 -2756.55 -4248.47 G, KJ/KG -40287.0 -38213.0 -31239.8 S, KJ/(KG)(K) 12.7487 12.7487 12.7487 M, (1/n) 20.149 20.332 20.616 (dLV/dLP)t -1.01279 -1.00794 -1.00077 (dLV/dLT)p 1.2469 1.1632 1.0199 Cp, KJ/(KG)(K) 4.1479 3.5302 2.2933 GAMMAs 1.1653 1.1748 1.2227 SON VEL,M/SEC 1219.0 1174.9 1038.4 MACH NUMBER 0.000 1.000 2.143 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2555 CSTAR, M/SEC 1757.1 1757.1 CF 0.6687 1.2663 Ivac, M/SEC 2175.0 2621.3 Isp, M/SEC 1174.9 2225.0 MOLE FRACTIONS *CO 0.43188 0.43243 0.42488 *CO2 0.06643 0.07039 0.08497 *H 0.03169 0.02170 0.00269 HCO 0.00001 0.00000 0.00000 *H2 0.21018 0.21633 0.23808 H2O 0.24498 0.25093 0.24899 *O 0.00119 0.00047 0.00000 *OH 0.01309 0.00752 0.00038 *O2 0.00055 0.00022 0.00000 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 1.90000 %FUEL= 34.482759 R,EQ.RATIO= 1.786671 PHI,EQ.RATIO= 1.786671 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7975 10.000 P, BAR 8.9632 4.9865 0.89632 T, K 3090.17 2758.65 1958.52 RHO, KG/CU M 7.0291-1 4.3805-1 1.1091-1 H, KJ/KG -891.29 -1598.23 -3254.79 U, KJ/KG -2166.44 -2736.58 -4062.96 G, KJ/KG -40287.0 -36767.5 -28223.4 S, KJ/(KG)(K) 12.7487 12.7487 12.7487 M, (1/n) 20.149 20.149 20.149 Cp, KJ/(KG)(K) 2.1464 2.1175 2.0130 GAMMAs 1.2380 1.2420 1.2579 SON VEL,M/SEC 1256.4 1189.1 1008.2 MACH NUMBER 0.000 1.000 2.156 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1602 CSTAR, M/SEC 1720.8 1720.8 CF 0.6910 1.2635 Ivac, M/SEC 2146.4 2545.9 Isp, M/SEC 1189.1 2174.2 MOLE FRACTIONS *CO 0.43188 *CO2 0.06643 *H 0.03169 HCO 0.00001 *H2 0.21018 H2O 0.24498 *O 0.00119 *OH 0.01309 *O2 0.00055 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.00000 %FUEL= 33.333333 R,EQ.RATIO= 1.697337 PHI,EQ.RATIO= 1.697337 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7473 10.000 P, BAR 8.9632 5.1296 0.89632 T, K 3177.59 2978.37 2330.79 RHO, KG/CU M 7.0062-1 4.3238-1 9.8456-2 H, KJ/KG -875.10 -1562.94 -3389.76 U, KJ/KG -2154.41 -2749.31 -4300.13 G, KJ/KG -40992.1 -39164.8 -32815.9 S, KJ/(KG)(K) 12.6250 12.6250 12.6250 M, (1/n) 20.652 20.874 21.287 (dLV/dLP)t -1.01818 -1.01222 -1.00170 (dLV/dLT)p 1.3462 1.2466 1.0418 Cp, KJ/(KG)(K) 4.8216 4.1305 2.4807 GAMMAs 1.1536 1.1596 1.2037 SON VEL,M/SEC 1214.8 1172.9 1046.8 MACH NUMBER 0.000 1.000 2.142 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2968 CSTAR, M/SEC 1767.4 1767.4 CF 0.6636 1.2689 Ivac, M/SEC 2184.4 2648.6 Isp, M/SEC 1172.9 2242.6 MOLE FRACTIONS *CO 0.41581 0.41617 0.41097 *CO2 0.07791 0.08285 0.09795 *H 0.03765 0.02814 0.00543 HCO 0.00001 0.00000 0.00000 *H2 0.18119 0.18567 0.20552 H2O 0.26284 0.27178 0.27886 *O 0.00256 0.00125 0.00002 *OH 0.02057 0.01341 0.00124 *O2 0.00145 0.00072 0.00001 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.00000 %FUEL= 33.333333 R,EQ.RATIO= 1.697337 PHI,EQ.RATIO= 1.697337 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7946 10.000 P, BAR 8.9632 4.9945 0.89632 T, K 3177.59 2842.50 2028.96 RHO, KG/CU M 7.0062-1 4.3643-1 1.0973-1 H, KJ/KG -875.10 -1583.12 -3254.14 U, KJ/KG -2154.41 -2727.52 -4071.01 G, KJ/KG -40992.1 -37469.6 -28869.6 S, KJ/(KG)(K) 12.6250 12.6250 12.6250 M, (1/n) 20.652 20.652 20.652 Cp, KJ/(KG)(K) 2.1262 2.0988 1.9993 GAMMAs 1.2336 1.2374 1.2521 SON VEL,M/SEC 1256.2 1190.0 1011.4 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1698 CSTAR, M/SEC 1725.9 1725.9 CF 0.6895 1.2639 Ivac, M/SEC 2151.7 2555.8 Isp, M/SEC 1190.0 2181.3 MOLE FRACTIONS *CO 0.41581 *CO2 0.07791 *H 0.03765 HCO 0.00001 *H2 0.18119 H2O 0.26284 *O 0.00256 *OH 0.02057 *O2 0.00145 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.10000 %FUEL= 32.258066 R,EQ.RATIO= 1.616512 PHI,EQ.RATIO= 1.616512 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7397 10.000 P, BAR 8.9632 5.1521 0.89632 T, K 3244.20 3060.25 2460.90 RHO, KG/CU M 7.0168-1 4.3277-1 9.6059-2 H, KJ/KG -859.95 -1542.99 -3397.98 U, KJ/KG -2137.33 -2733.47 -4331.07 G, KJ/KG -41421.4 -39804.5 -34166.0 S, KJ/(KG)(K) 12.5027 12.5027 12.5027 M, (1/n) 21.117 21.373 21.928 (dLV/dLP)t -1.02447 -1.01767 -1.00333 (dLV/dLT)p 1.4612 1.3519 1.0793 Cp, KJ/(KG)(K) 5.5745 4.8631 2.7894 GAMMAs 1.1446 1.1475 1.1835 SON VEL,M/SEC 1209.2 1168.8 1050.8 MACH NUMBER 0.000 1.000 2.144 PERFORMANCE PARAMETERS Ae/At 1.0000 2.3372 CSTAR, M/SEC 1772.0 1772.0 CF 0.6596 1.2714 Ivac, M/SEC 2187.4 2667.2 Isp, M/SEC 1168.8 2253.0 MOLE FRACTIONS *CO 0.39910 0.39877 0.39445 *CO2 0.08944 0.09571 0.11288 *H 0.04187 0.03334 0.00935 HCO 0.00001 0.00000 0.00000 HO2 0.00001 0.00000 0.00000 *H2 0.15668 0.15931 0.17516 H2O 0.27605 0.28747 0.30476 *O 0.00462 0.00265 0.00011 *OH 0.02905 0.02085 0.00321 *O2 0.00317 0.00188 0.00008 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.10000 %FUEL= 32.258066 R,EQ.RATIO= 1.616512 PHI,EQ.RATIO= 1.616512 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7923 10.000 P, BAR 8.9632 5.0010 0.89632 T, K 3244.20 2906.90 2084.02 RHO, KG/CU M 7.0168-1 4.3693-1 1.0923-1 H, KJ/KG -859.95 -1565.91 -3241.78 U, KJ/KG -2137.33 -2710.48 -4062.35 G, KJ/KG -41421.4 -37910.1 -29297.8 S, KJ/(KG)(K) 12.5027 12.5027 12.5027 M, (1/n) 21.117 21.117 21.117 Cp, KJ/(KG)(K) 2.1056 2.0794 1.9843 GAMMAs 1.2300 1.2336 1.2476 SON VEL,M/SEC 1253.5 1188.2 1011.8 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1777 CSTAR, M/SEC 1726.4 1726.4 CF 0.6883 1.2642 Ivac, M/SEC 2151.5 2558.5 Isp, M/SEC 1188.2 2182.6 MOLE FRACTIONS *CO 0.39910 *CO2 0.08944 *H 0.04187 HCO 0.00001 HO2 0.00001 *H2 0.15668 H2O 0.27605 *O 0.00462 *OH 0.02905 *O2 0.00317 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.20000 %FUEL= 31.250000 R,EQ.RATIO= 1.543034 PHI,EQ.RATIO= 1.543034 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7340 10.000 P, BAR 8.9632 5.1692 0.89632 T, K 3293.59 3121.76 2572.53 RHO, KG/CU M 7.0523-1 4.3479-1 9.4402-2 H, KJ/KG -845.76 -1522.48 -3393.10 U, KJ/KG -2116.71 -2711.37 -4342.57 G, KJ/KG -41630.7 -40179.7 -35249.1 S, KJ/(KG)(K) 12.3831 12.3831 12.3831 M, (1/n) 21.546 21.832 22.528 (dLV/dLP)t -1.03120 -1.02404 -1.00598 (dLV/dLT)p 1.5835 1.4741 1.1397 Cp, KJ/(KG)(K) 6.3459 5.6828 3.2706 GAMMAs 1.1380 1.1384 1.1636 SON VEL,M/SEC 1202.6 1163.4 1051.1 MACH NUMBER 0.000 1.000 2.147 PERFORMANCE PARAMETERS Ae/At 1.0000 2.3739 CSTAR, M/SEC 1772.0 1772.0 CF 0.6565 1.2738 Ivac, M/SEC 2185.3 2677.8 Isp, M/SEC 1163.4 2257.1 MOLE FRACTIONS *CO 0.38225 0.38092 0.37548 *CO2 0.10066 0.10839 0.12944 *H 0.04439 0.03694 0.01395 HCO 0.00001 0.00000 0.00000 HO2 0.00001 0.00001 0.00000 *H2 0.13635 0.13736 0.14784 H2O 0.28535 0.29855 0.32562 *O 0.00728 0.00472 0.00042 *OH 0.03776 0.02909 0.00688 *O2 0.00592 0.00402 0.00038 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.20000 %FUEL= 31.250000 R,EQ.RATIO= 1.543034 PHI,EQ.RATIO= 1.543034 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7904 10.000 P, BAR 8.9632 5.0062 0.89632 T, K 3293.59 2955.11 2126.11 RHO, KG/CU M 7.0523-1 4.3901-1 1.0925-1 H, KJ/KG -845.76 -1547.36 -3220.79 U, KJ/KG -2116.71 -2687.71 -4041.23 G, KJ/KG -41630.7 -38140.9 -29548.7 S, KJ/(KG)(K) 12.3831 12.3831 12.3831 M, (1/n) 21.546 21.546 21.546 Cp, KJ/(KG)(K) 2.0850 2.0599 1.9682 GAMMAs 1.2271 1.2305 1.2439 SON VEL,M/SEC 1248.8 1184.6 1010.2 MACH NUMBER 0.000 1.000 2.157 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1841 CSTAR, M/SEC 1723.5 1723.5 CF 0.6873 1.2645 Ivac, M/SEC 2147.2 2555.9 Isp, M/SEC 1184.6 2179.5 MOLE FRACTIONS *CO 0.38225 *CO2 0.10066 *H 0.04439 HCO 0.00001 HO2 0.00001 *H2 0.13635 H2O 0.28535 *O 0.00728 *OH 0.03776 *O2 0.00592 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.30000 %FUEL= 30.303031 R,EQ.RATIO= 1.475946 PHI,EQ.RATIO= 1.475946 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7299 10.000 P, BAR 8.9632 5.1814 0.89632 T, K 3329.41 3166.62 2662.40 RHO, KG/CU M 7.1054-1 4.3794-1 9.3437-2 H, KJ/KG -832.42 -1502.02 -3377.41 U, KJ/KG -2093.87 -2685.15 -4336.68 G, KJ/KG -41673.7 -40346.4 -36036.6 S, KJ/(KG)(K) 12.2668 12.2668 12.2668 M, (1/n) 21.945 22.254 23.076 (dLV/dLP)t -1.03782 -1.03079 -1.01003 (dLV/dLT)p 1.7030 1.6024 1.2309 Cp, KJ/(KG)(K) 7.0698 6.5113 3.9759 GAMMAs 1.1333 1.1319 1.1458 SON VEL,M/SEC 1195.7 1157.2 1048.4 MACH NUMBER 0.000 1.000 2.152 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4042 CSTAR, M/SEC 1768.6 1768.6 CF 0.6543 1.2757 Ivac, M/SEC 2179.6 2681.3 Isp, M/SEC 1157.2 2256.1 MOLE FRACTIONS *CO 0.36563 0.36317 0.35479 *CO2 0.11130 0.12048 0.14674 *H 0.04552 0.03900 0.01836 HCO 0.00001 0.00000 0.00000 HO2 0.00002 0.00001 0.00000 *H2 0.11963 0.11941 0.12442 H2O 0.29159 0.30590 0.34085 *O 0.01036 0.00732 0.00117 *OH 0.04612 0.03736 0.01237 *O2 0.00980 0.00734 0.00129 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.30000 %FUEL= 30.303031 R,EQ.RATIO= 1.475946 PHI,EQ.RATIO= 1.475946 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7889 10.000 P, BAR 8.9632 5.0105 0.89632 T, K 3329.41 2990.52 2157.80 RHO, KG/CU M 7.1054-1 4.4221-1 1.0963-1 H, KJ/KG -832.42 -1528.13 -3193.88 U, KJ/KG -2093.87 -2661.18 -4011.43 G, KJ/KG -41673.7 -38212.2 -29663.2 S, KJ/(KG)(K) 12.2668 12.2668 12.2668 M, (1/n) 21.945 21.945 21.945 Cp, KJ/(KG)(K) 2.0646 2.0404 1.9515 GAMMAs 1.2248 1.2280 1.2409 SON VEL,M/SEC 1243.0 1179.6 1007.2 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1893 CSTAR, M/SEC 1718.3 1718.3 CF 0.6865 1.2648 Ivac, M/SEC 2140.1 2549.4 Isp, M/SEC 1179.6 2173.2 MOLE FRACTIONS *CO 0.36563 *CO2 0.11130 *H 0.04552 HCO 0.00001 HO2 0.00002 *H2 0.11963 H2O 0.29159 *O 0.01036 *OH 0.04612 *O2 0.00980 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.40000 %FUEL= 29.411764 R,EQ.RATIO= 1.414448 PHI,EQ.RATIO= 1.414448 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7270 10.000 P, BAR 8.9632 5.1900 0.89632 T, K 3354.90 3198.63 2729.91 RHO, KG/CU M 7.1707-1 4.4188-1 9.3076-2 H, KJ/KG -819.86 -1481.95 -3353.59 U, KJ/KG -2069.82 -2656.48 -4316.58 G, KJ/KG -41595.9 -40358.6 -36533.3 S, KJ/(KG)(K) 12.1542 12.1542 12.1542 M, (1/n) 22.316 22.643 23.570 (dLV/dLP)t -1.04386 -1.03728 -1.01556 (dLV/dLT)p 1.8117 1.7252 1.3542 Cp, KJ/(KG)(K) 7.6988 7.2722 4.8967 GAMMAs 1.1299 1.1274 1.1319 SON VEL,M/SEC 1188.4 1150.7 1044.0 MACH NUMBER 0.000 1.000 2.156 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4268 CSTAR, M/SEC 1762.7 1762.7 CF 0.6528 1.2771 Ivac, M/SEC 2171.4 2678.9 Isp, M/SEC 1150.7 2251.1 MOLE FRACTIONS *CO 0.34950 0.34591 0.33357 *CO2 0.12124 0.13173 0.16363 *H 0.04562 0.03984 0.02181 HCO 0.00001 0.00000 0.00000 HO2 0.00003 0.00002 0.00000 *H2 0.10585 0.10479 0.10528 H2O 0.29556 0.31047 0.35075 *O 0.01365 0.01026 0.00250 *OH 0.05378 0.04511 0.01909 *O2 0.01476 0.01188 0.00336 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.40000 %FUEL= 29.411764 R,EQ.RATIO= 1.414448 PHI,EQ.RATIO= 1.414448 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7876 10.000 P, BAR 8.9632 5.0140 0.89632 T, K 3354.90 3016.12 2181.45 RHO, KG/CU M 7.1707-1 4.4619-1 1.1028-1 H, KJ/KG -819.86 -1508.72 -3163.25 U, KJ/KG -2069.82 -2632.46 -3976.01 G, KJ/KG -41595.9 -38167.2 -29676.9 S, KJ/(KG)(K) 12.1542 12.1542 12.1542 M, (1/n) 22.316 22.316 22.316 Cp, KJ/(KG)(K) 2.0448 2.0212 1.9347 GAMMAs 1.2228 1.2260 1.2385 SON VEL,M/SEC 1236.3 1173.8 1003.3 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1936 CSTAR, M/SEC 1711.5 1711.5 CF 0.6858 1.2649 Ivac, M/SEC 2131.1 2540.3 Isp, M/SEC 1173.8 2164.9 MOLE FRACTIONS *CO 0.34950 *CO2 0.12124 *H 0.04562 HCO 0.00001 HO2 0.00003 *H2 0.10585 H2O 0.29556 *O 0.01365 *OH 0.05378 *O2 0.01476 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.50000 %FUEL= 28.571429 R,EQ.RATIO= 1.357870 PHI,EQ.RATIO= 1.357870 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7250 10.000 P, BAR 8.9632 5.1960 0.89632 T, K 3372.62 3221.02 2777.85 RHO, KG/CU M 7.2442-1 4.4634-1 9.3186-2 H, KJ/KG -808.03 -1462.42 -3324.32 U, KJ/KG -2045.31 -2626.56 -4286.18 G, KJ/KG -41432.6 -40261.0 -36784.7 S, KJ/(KG)(K) 12.0454 12.0454 12.0454 M, (1/n) 22.664 23.005 24.012 (dLV/dLP)t -1.04903 -1.04306 -1.02204 (dLV/dLT)p 1.9050 1.8343 1.4971 Cp, KJ/(KG)(K) 8.2121 7.9177 5.9249 GAMMAs 1.1275 1.1243 1.1223 SON VEL,M/SEC 1181.1 1144.0 1039.0 MACH NUMBER 0.000 1.000 2.159 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4426 CSTAR, M/SEC 1755.4 1755.4 CF 0.6517 1.2780 Ivac, M/SEC 2161.6 2672.1 Isp, M/SEC 1144.0 2243.3 MOLE FRACTIONS *CO 0.33397 0.32934 0.31287 *CO2 0.13044 0.14206 0.17919 *H 0.04499 0.03979 0.02402 HCO 0.00001 0.00000 0.00000 HO2 0.00004 0.00003 0.00000 *H2 0.09441 0.09279 0.09010 H2O 0.29785 0.31303 0.35639 *O 0.01698 0.01333 0.00438 *OH 0.06057 0.05207 0.02610 *O2 0.02073 0.01754 0.00695 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.50000 %FUEL= 28.571429 R,EQ.RATIO= 1.357870 PHI,EQ.RATIO= 1.357870 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7866 10.000 P, BAR 8.9632 5.0169 0.89632 T, K 3372.62 3034.34 2198.96 RHO, KG/CU M 7.2442-1 4.5068-1 1.1111-1 H, KJ/KG -808.03 -1489.46 -3130.49 U, KJ/KG -2045.31 -2602.63 -3937.20 G, KJ/KG -41432.6 -38039.3 -29617.9 S, KJ/(KG)(K) 12.0454 12.0454 12.0454 M, (1/n) 22.664 22.664 22.664 Cp, KJ/(KG)(K) 2.0256 2.0025 1.9180 GAMMAs 1.2212 1.2243 1.2365 SON VEL,M/SEC 1229.2 1167.4 998.8 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.1972 CSTAR, M/SEC 1703.6 1703.6 CF 0.6853 1.2651 Ivac, M/SEC 2121.0 2529.5 Isp, M/SEC 1167.4 2155.2 MOLE FRACTIONS *CO 0.33397 *CO2 0.13044 *H 0.04499 HCO 0.00001 HO2 0.00004 *H2 0.09441 H2O 0.29785 *O 0.01698 *OH 0.06057 *O2 0.02073 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.60000 %FUEL= 27.777779 R,EQ.RATIO= 1.305644 PHI,EQ.RATIO= 1.305644 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7236 10.000 P, BAR 8.9632 5.2002 0.89632 T, K 3384.51 3236.31 2810.76 RHO, KG/CU M 7.3231-1 4.5113-1 9.3624-2 H, KJ/KG -796.85 -1443.52 -3291.78 U, KJ/KG -2020.81 -2596.22 -4249.13 G, KJ/KG -41210.0 -40087.0 -36854.0 S, KJ/(KG)(K) 11.9406 11.9406 11.9406 M, (1/n) 22.991 23.344 24.411 (dLV/dLP)t -1.05326 -1.04789 -1.02856 (dLV/dLT)p 1.9816 1.9256 1.6398 Cp, KJ/(KG)(K) 8.6090 8.4312 6.9120 GAMMAs 1.1257 1.1220 1.1160 SON VEL,M/SEC 1173.8 1137.3 1033.6 MACH NUMBER 0.000 1.000 2.161 PERFORMANCE PARAMETERS Ae/At 1.0000 2.4532 CSTAR, M/SEC 1747.0 1747.0 CF 0.6510 1.2786 Ivac, M/SEC 2150.8 2662.4 Isp, M/SEC 1137.3 2233.8 MOLE FRACTIONS *CO 0.31911 0.31356 0.29329 *CO2 0.13892 0.15150 0.19304 *H 0.04389 0.03915 0.02512 HCO 0.00001 0.00000 0.00000 HO2 0.00005 0.00003 0.00001 *H2 0.08481 0.08285 0.07811 H2O 0.29893 0.31416 0.35905 *O 0.02021 0.01637 0.00658 *OH 0.06649 0.05816 0.03268 *O2 0.02756 0.02421 0.01212 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION Pinj = 130.0 PSIA CASE = 1 REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) KJ/KG-MOL K FUEL Jet-A(L) 1.0000000 -303521.711 298.000 OXIDANT O2(L) 1.0000000 -12979.000 90.000 O/F= 2.60000 %FUEL= 27.777779 R,EQ.RATIO= 1.305644 PHI,EQ.RATIO= 1.305644 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7857 10.000 P, BAR 8.9632 5.0194 0.89632 T, K 3384.51 3046.98 2211.81 RHO, KG/CU M 7.3231-1 4.5552-1 1.1206-1 H, KJ/KG -796.85 -1470.58 -3096.70 U, KJ/KG -2020.81 -2572.47 -3896.56 G, KJ/KG -41210.0 -37853.3 -29507.0 S, KJ/(KG)(K) 11.9406 11.9406 11.9406 M, (1/n) 22.991 22.991 22.991 Cp, KJ/(KG)(K) 2.0071 1.9844 1.9016 GAMMAs 1.2198 1.2229 1.2348 SON VEL,M/SEC 1221.9 1160.8 993.8 MACH NUMBER 0.000 1.000 2.158 PERFORMANCE PARAMETERS Ae/At 1.0000 2.2002 CSTAR, M/SEC 1695.1 1695.1 CF 0.6848 1.2652 Ivac, M/SEC 2110.1 2517.6 Isp, M/SEC 1160.8 2144.7 MOLE FRACTIONS *CO 0.31911 *CO2 0.13892 *H 0.04389 HCO 0.00001 HO2 0.00005 *H2 0.08481 H2O 0.29893 *O 0.02021 *OH 0.06649 *O2 0.02756 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS