Investigation of Plume Induced Separation on a Full-Size Missile at Supersonic Velocities
Investigation of Plume Induced Separation on a Full-Size Missile at Supersonic Velocities
- New search for: T. A. Martin
- New search for: T. A. Martin
A large amount of data to determine plume effects have been obtained from various simulation techniques. To provide data for evaluating the adequacy of these simulations, a test utilizing a rocket sled to measure surface pressures on a full-size, live, high thrust rocket at Mach number up to Moo 1.6. Selected portions of the data are presented to show Mach number and thrust level effects.
Document information
Investigation of Plume Induced Separation on a Full-Size Missile at Supersonic Velocities
1980
26 pages
Report
No indication
English
Missile Technology , Rocket Engines & Motors , Combustion & Ignition , ROCKET ENGINES , Plumes , Exhaust plumes , Flow separation , Base pressure , Gas flow , Supersonic flow , Guided missiles , Exhaust gases , Rocket sleds , Pressure measurement , Surface properties , Test vehicles , Free stream , Separation , Fin stabilized ammunition
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