Accession Number:

ADA017712

Title:

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

Descriptive Note:

Corporate Author:

TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Report Date:

1975-06-01

Pagination or Media Count:

61.0

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.

Subject Categories:

  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE