Experimental Study of an Underexpanded, Supersonic Nozzle Exhausting into a Constrictive Launch Tube,
TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
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The present report discusses launcher flow-field data from complementary cold-gas test programs conducted at the University of Texas at Austin. Based on these data, flow-field models for the constrictive launcher configurations have been defined as a function of the nozzle-exit location and of the stagnation pressure in the nozzle reservoir. The conclusions are based on the configurations of the present experimental program.
- Combustion and Ignition
- Rocket Engines