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Rocket Propellant Properties: 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 |
|---|---|---|---|---|---|---|---|---|---|---|---|
| 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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