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Rocket Propellant Properties: solid star27
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) | density g cm3 (g/cm3) | expansion ratio (dimensionless) | fuel | hazard class | isp vac s (s) | metal content pct (%) | mol mass exhaust kg mol (kg/mol) | oxidizer | propellant type | source method |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| solid star27 | 3,538 | 48 | 5,180 | 1,579 | 1.78 | 552 | HTPB type AP Al binder | 1.3 | 290.8 | 16 | 6,368 | AP integral | solid composite | STAR 27 apogee motor (Orbital ATK). 72% AP / 16% Al / 12% binder. Pc avg=552 psia burn-time average (max 569 psia). Vacuum Isp=290.8 s. C*=5180 ft/s (1579 m/s). Tc=5909 F (3538 K) adiabatic flame. Burn time 34.35 s. Eight-point star grain. Expansion ratio 48.8:1. |
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