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Rocket Propellant Properties: lox propylene
Rocket propellant performance data — specific impulse, characteristic velocity, chamber conditions for bipropellant, solid, and monopropellant combinations
| propellant id | chamber pressure psia (psia) | chamber temp deg r (deg R) | chamber temp k (K) | cstar ft s (ft/s) | cstar m s (m/s) | expansion ratio (dimensionless) | fuel | isp vac s (s) | mixture ratio (dimensionless) | oxidizer | source method |
|---|---|---|---|---|---|---|---|---|---|---|---|
| lox propylene | 1,000 | 6,916 | 3,842 | 5,938 | 1,810 | 100 | Propylene | 364 | 2.3 | LOX | LOX/Propylene (C3H6), Pc=1000 psia, epsilon=100:1, MR=2.3 (O/F), equilibrium flow. Isp vac=364 s, Tc=3842 K per NSS liquid fuels reference table. C*=1810 m/s estimated via RPE9 hydrocarbon correlation. Higher combustion temperature than LOX/RP-1 (3803 K) increases cooling challenge. Density Isp comparable to RP-1; bulk density 903 kg/m3 at NBP 225 K. |
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