a-1

Engine name: A-1 Tue Mar 10 04:51:26 2015 Propellant Specification Component Temperature (K) Mass fraction Mole fraction RP-1 298.15 0.30 0.49 O2(L) 90.17 0.70 0.51 Total 1.00 1.00 Exploded propellant formula: O1.013 C0.493 H0.962 O/F = 2.350 O/F 0 = 3.406 (stoichiometric) αox = 0.690 (oxidizer excess coefficient) Table 1. Thermodynamic properties Parameter Injector Nozzle inlet Nozzle throat Nozzle exit Unit Pressure 7.5498 6.3748 4.0190 0.0598 MPa Temperature 3607.4809 3563.6454 3394.6274 1880.5353 K Enthalpy -812.4596 -933.3756 -1521.2999 -5465.3553 kJ/kg Entropy 11.4677 11.4963 11.4963 11.4963 kJ/(kg·K) Specific heat (p=const) 5.1776 5.1805 4.8031 2.0029 kJ/(kg·K) Specific heat (V=const) 4.3947 4.4028 4.1039 1.6500 kJ/(kg·K) Gas constant 0.3687 0.3682 0.3645 0.3508 kJ/(kg·K) Molecular weight 22.5532 22.5806 22.8086 23.7016 Isentropic exponent 1.1467 1.1459 1.1456 1.2138 Density 5.6768 4.8582 3.2478 0.0906 kg/m³ Sonic velocity 1234.9064 1226.2043 1190.6554 894.8274 m/s Velocity 0.0000 491.7642 1190.6554 3050.5395 m/s Mach number 0.0000 0.4010 1.0000 3.4091 Area ratio 1.6000 1.6000 1.0000 14.0000 Mass flux 2389.0951 2389.0951 3867.0468 276.3302 kg/(m²·s) Table 2. Fractions of the combustion products Species Injector mass fractions Injector mole fractions Nozzle inlet mass fractions Nozzle inlet mole fractions Nozzle throat mass fractions Nozzle throat mole fractions Nozzle exit mass fractions Nozzle exit mole fractions CO 0.4458328 0.3589765 0.4445909 0.3584115 0.4369910 0.3558416 0.3793073 0.3209619 CO2 0.2393605 0.1226633 0.2413278 0.1238217 0.2533073 0.1312805 0.3439998 0.1852630 COOH 0.0000372 0.0000186 0.0000320 0.0000161 0.0000198 0.0000100 H 0.0012877 0.0288122 0.0012733 0.0285265 0.0010767 0.0243643 0.0000144 0.0003384 H2 0.0099839 0.1116980 0.0099750 0.1117341 0.0098628 0.1115922 0.0123948 0.1457315 H2O 0.2570992 0.3218610 0.2578170 0.3231518 0.2639619 0.3341943 0.2642313 0.3476324 H2O2 0.0000129 0.0000085 0.0000111 0.0000074 0.0000064 0.0000043 HCHO,formaldehy 0.0000017 0.0000013 0.0000014 0.0000011 0.0000009 0.0000007 1

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Engine name: A-1Tue Mar 10 04:51:26 2015

Propellant SpecificationComponent Temperature (K) Mass fraction Mole fraction

RP-1 298.15 0.30 0.49O2(L) 90.17 0.70 0.51

Total 1.00 1.00

Exploded propellant formula: O1.013 C0.493 H0.962 O/F = 2.350

O/F0 = 3.406 (stoichiometric)ox = 0.690 (oxidizer excess coefficient)

Table 1. Thermodynamic propertiesParameter Injector Nozzle inlet Nozzle throat Nozzle exit UnitPressure 7.5498 6.3748 4.0190 0.0598 MPaTemperature 3607.4809 3563.6454 3394.6274 1880.5353 KEnthalpy -812.4596 -933.3756 -1521.2999 -5465.3553 kJ/kgEntropy 11.4677 11.4963 11.4963 11.4963 kJ/(kgK)Specific heat (p=const) 5.1776 5.1805 4.8031 2.0029 kJ/(kgK)Specific heat (V=const) 4.3947 4.4028 4.1039 1.6500 kJ/(kgK)Gas constant 0.3687 0.3682 0.3645 0.3508 kJ/(kgK)Molecular weight 22.5532 22.5806 22.8086 23.7016Isentropic exponent 1.1467 1.1459 1.1456 1.2138Density 5.6768 4.8582 3.2478 0.0906 kg/mSonic velocity 1234.9064 1226.2043 1190.6554 894.8274 m/sVelocity 0.0000 491.7642 1190.6554 3050.5395 m/sMach number 0.0000 0.4010 1.0000 3.4091Area ratio 1.6000 1.6000 1.0000 14.0000Mass flux 2389.0951 2389.0951 3867.0468 276.3302 kg/(ms)

Table 2. Fractions of the combustion productsSpecies Injector

massfractions

Injectormole

fractions

Nozzleinlet

massfractions

Nozzleinletmole

fractions

Nozzlethroatmass

fractions

Nozzlethroat

molefractions

Nozzle exitmass

fractions

Nozzle exitmole

fractions

CO 0.4458328 0.3589765 0.4445909 0.3584115 0.4369910 0.3558416 0.3793073 0.3209619CO2 0.2393605 0.1226633 0.2413278 0.1238217 0.2533073 0.1312805 0.3439998 0.1852630COOH 0.0000372 0.0000186 0.0000320 0.0000161 0.0000198 0.0000100H 0.0012877 0.0288122 0.0012733 0.0285265 0.0010767 0.0243643 0.0000144 0.0003384H2 0.0099839 0.1116980 0.0099750 0.1117341 0.0098628 0.1115922 0.0123948 0.1457315H2O 0.2570992 0.3218610 0.2578170 0.3231518 0.2639619 0.3341943 0.2642313 0.3476324H2O2 0.0000129 0.0000085 0.0000111 0.0000074 0.0000064 0.0000043HCHO,formaldehy 0.0000017 0.0000013 0.0000014 0.0000011 0.0000009 0.0000007

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Species Injectormass

fractions

Injectormole

fractions

Nozzleinlet

massfractions

Nozzleinletmole

fractions

Nozzlethroatmass

fractions

Nozzlethroat

molefractions

Nozzle exitmass

fractions

Nozzle exitmole

fractions

HCO 0.0000455 0.0000353 0.0000391 0.0000305 0.0000236 0.0000185HCOOH 0.0000069 0.0000034 0.0000058 0.0000029 0.0000037 0.0000018HO2 0.0000629 0.0000430 0.0000558 0.0000382 0.0000314 0.0000217O 0.0042583 0.0060026 0.0041027 0.0057903 0.0028355 0.0040423 0.0000001 0.0000001O2 0.0093894 0.0066178 0.0090983 0.0064204 0.0065660 0.0046802 0.0000002 0.0000001OH 0.0326210 0.0432583 0.0316693 0.0420474 0.0253131 0.0339475 0.0000520 0.0000725

Table 3. Theoretical (ideal) performanceParameter Sea level Optimum expansion Vacuum UnitCharacteristic velocity 1806.66 m/sEffective exhaust velocity 2900.11 3050.54 3266.79 m/sSpecific impulse (by mass) 2900.11 3050.54 3266.79 Ns/kgSpecific impulse (by weight) 295.73 311.07 333.12 sThrust coefficient 1.6052 1.6885 1.8082

Table 4. Estimated delivered performanceParameter Sea level Optimum expansion Vacuum UnitCharacteristic velocity 1780.24 m/sEffective exhaust velocity 2776.25 2926.67 3142.93 m/sSpecific impulse (by mass) 2776.25 2926.67 3142.93 Ns/kgSpecific impulse (by weight) 283.10 298.44 320.49 sThrust coefficient 1.5595 1.6440 1.7655

Ambient condition for optimum expansion: H=4.24 km, p=0.590 atm

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