Accession Number : ADA017712

Title :   Experimental Study of an Underexpanded, Supersonic Nozzle Exhausting into a Constrictive Launch Tube,

Corporate Author : TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Personal Author(s) : Bertin,John J. ; Morris,Robert R. ; Garms,Gena M. ; Motal,M. Reeves ; Faria,H. Tom

Report Date : JUN 1975

Pagination or Media Count : 61

Abstract : 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.

Descriptors :   *Supersonic nozzles, *Rocket nozzles, *Launch tubes, *Rocket exhaust, Exhaust gases, Nozzle gas flow, Flow fields, Schlieren photography, Expansion

Subject Categories : Combustion and Ignition
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE