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Rocket Propellant Properties: mono hydrazine
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) | oxidizer | source method |
|---|---|---|---|---|---|---|---|---|---|---|
| mono hydrazine | 200 | 1,800 | 1,000 | 4,167 | 1,270 | 40 | N2H4 | 235 | none monopropellant | Hydrazine monopropellant catalytic decomposition (Shell 405 catalyst). Pc=200 psia, epsilon=40:1 nozzle. Isp vac=235 s at 30-40% NH3 dissociation (RPE9 / MIT OCW 16.522 Lecture 12). Higher dissociation lowers Tc but also lowers Isp; 30-40% is practical optimum. C*=1270 m/s, Tc=1000 K at ~30% NH3 dissociation. Actual delivered Isp for 1-N class thrusters: 220-235 s. Carcinogen (REACH / OSHA); being replaced by green alternatives. |
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