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Rocket Propellant Properties: n2o4 rp1
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 |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| n2o4 rp1 | 1.23 | 1,000 | 5,922 | 3,290 | 5,613 | 1,711 | 40 | RP1 | 1.23 | 278 | 297 | 0 | 3.4 | 22.6 | N2O4 | liquid bipropellant | Sutton Table 5-5 standard conditions: Pc=1000 psia optimum stoichiometry. Is shifting=297 s Is frozen=278 s c*=1711 m/s Tc=3290 K m=22.6 kg/mol k=1.23. |
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