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Rocket Propellant Properties: n2o ethanol
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 |
|---|---|---|---|---|---|---|---|---|---|---|---|
| n2o ethanol | 200 | 5,130 | 2,850 | 5,217 | 1,590 | 10 | Ethanol | 265 | 5.75 | N2O | N2O/Ethanol liquid bipropellant, Pc=200 psia, epsilon=10:1, MR=5.75 (O/F). Experimental Isp 250-260 s (OSTI 1492388); NASA CEA theoretical ~270 s. Isp vac=265 s is a representative mid-range delivered value. N2O is self-pressurizing; low-cost small-satellite and student launcher propellant. Not hypergolic; requires ignition source. |
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