Rocket Propellant Properties: lox_ch4 to 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_ch4 | 300 | 6,300 | 3,500 | 6,100 | 1,859.28 | 40 | CH4 | 370 | 3.4 | LOX | Fallback seed (RocketCEA package unavailable) |
| lox_lh2 | 300 | 6,200 | 3,444.4444 | 7,700 | 2,346.96 | 40 | LH2 | 450 | 5.5 | LOX | Fallback seed (RocketCEA package unavailable) |
| lox_lh2_ssme | 3,200 | 6,556 | 3,642 | 7,988 | 2,435 | 77.5 | LH2 | 453 | 6 | LOX | SSME delivered performance; Pc=3200 psia, epsilon=77.5:1, MR=6.0. Isp_vac=453 s (delivered, ~97% of theoretical). C*=2435 m/s, Tc=3642 K from Astronautix/RPE9. |
| 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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