Rocket Propellant Properties: lox_rp1 to n2o4_n2h4
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_rp1 | 300 | 6,500 | 3,611.1111 | 5,900 | 1,798.32 | 40 | RP1 | 350 | 2.6 | LOX | Fallback seed (RocketCEA package unavailable) |
| n2o4_aerozine50 | 800 | 6,178 | 3,432 | 5,659 | 1,725 | 15 | Aerozine-50 | 320 | 1.93 | N2O4 | LR87-5 engine (Titan II 1st stage) flight MR=1.93; Isp_vac=320 s is delivered vacuum Isp for sea-level-optimized nozzle (epsilon~15, Pc~800 psia). Theoretical optimum at 40:1 is ~323 s. Aerozine-50 = 50/50 wt% UDMH/N2H4. Hypergolic storable. |
| n2o4_mmh | 300 | 5,800 | 3,222.2222 | 5,600 | 1,706.88 | 40 | MMH | 330 | 2.1 | N2O4 | Fallback seed (RocketCEA package unavailable) |
| n2o4_n2h4 | 1,000 | 5,913 | 3,285 | 5,709 | 1,740 | 40 | N2H4 | 335 | 1.3 | N2O4 | Theoretical optimum, Pc=1000 psia, epsilon=40:1, MR=1.30 (O/F). Isp_vac=335 s per RPE9 Table 5-4; AMBR engine demonstrated >=333.5 s. Hypergolic storable; widely used for spacecraft apogee kick and attitude control. |
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