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Rocket Propellant Properties: h2o2 rp1
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 |
|---|---|---|---|---|---|---|---|---|---|---|---|
| h2o2 rp1 | 1,000 | 5,355 | 2,975 | 5,462 | 1,665 | 40 | RP1 | 319 | 7.07 | H2O2 90pct | 90% H2O2 / RP-1, theoretical optimum Pc=1000 psia, epsilon=40:1, MR=7.07 (O/F). Isp vac=319 s, C*=1665 m/s, Tc=2975 K. Isp drops to ~305 s with 90% C* efficiency (real engine). Gamma-301 (Black Arrow) delivered ~265 s sea-level. Non-hypergolic; H2O2 catalytically pre-decomposed to ignite RP-1. |
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