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Rocket Propellant Properties: h2o2 aerozine50
Rocket propellant performance data — specific impulse, characteristic velocity, chamber conditions for bipropellant, solid, and monopropellant combinations
| propellant id | avg specific gravity (dimensionless) | 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 | gamma exhaust (dimensionless) | isp frozen s (s) | isp shifting s (s) | metal content pct (%) | mixture ratio (dimensionless) | mol mass exhaust kg mol (kg/mol) | oxidizer | propellant type | source method |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| h2o2 aerozine50 | 1.27 | 1,000 | 5,710 | 3,172 | 5,580 | 1,701 | 40 | Aerozine-50 | 1.22 | 272 | 279 | 0 | 2.2 | 22.4 | H2O2 90pct | liquid bipropellant | Sutton Table 5-5 standard conditions: Pc=1000 psia optimum stoichiometry. 90% H2O2 / Aerozine-50 (50% UDMH + 50% N2H4). Is shifting=279 s Is frozen=272 s c*=1701 m/s Tc=3172 K m=22.4 kg/mol k=1.22. |
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