Sample data from Engineering Database — 375 reference tables, deterministic calculators, and Engineering AI. Sign up free
Rocket Propellant Properties: n2o4 aerozine50
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 |
|---|---|---|---|---|---|---|---|---|---|---|---|
| n2o4 aerozine50 | 800 | 6,178 | 3,432 | 5,659 | 1,725 | 15 | Aerozine-50 | 320 | 1.93 | N2O4 | LR87-5 engine (Titan II 1st stage) flight MR=1.93; Isp vac=320 s is delivered vacuum Isp for sea-level-optimized nozzle (epsilon~15, Pc~800 psia). Theoretical optimum at 40:1 is ~323 s. Aerozine-50 = 50/50 wt% UDMH/N2H4. Hypergolic storable. |
What else is in Engineering Database
Iron Engine ↗Engineering AI at ironengine.ai
AI built for engineering. Searches the engineering database, performs calculations, gives source-backed engineering insights.
Get started for free ↗Reference Data375 engineering tablesMaterial properties, pipe and shape dimensions, code tables, and electrical ratings across mechanical, civil, chemical, electrical, materials, and manufacturing engineering.
Browse dataCalculatorsDeterministic engineering calculatorsSizing, checking, and conversion tools that run against the reference tables. Inputs are code-compliant, outputs are traceable to the source standard.
Browse calculators