Accession Number : AD0752896

Title :   Results of Transonic Wind Tunnel Investigations to Determine the Effects of Nozzle Geometry and Jet Plume on the Aerodynamics of a Body of Revolution.

Descriptive Note : Technical rept.,

Corporate Author : CHRYSLER CORP NEW ORLEANS LA SPACE DIV

Personal Author(s) : Henderson,James H. ; Vaughn,John E.

Report Date : NOV 1972

Pagination or Media Count : 256

Abstract : A transonic wind tunnel test was conducted by the Army Missile Command, Redstone Arsenal, on a base drag research missile model in the Cornell Aeronautical Laboratory (CAL) 8-Foot Transonic Wind Tunnel during June 1972. The test was conducted to investigate the effects of nozzle geometry on jet plume characteristics at high thrust levels and to study the effects of nozzle geometry on base pressure at low thrust levels. Model external and nozzle internal static pressure measurements were obtained on all nozzles. This report presents details of the test program, an outline of the test procedures and the results of the investigations in plotted form. (Author)

Descriptors :   (*ROCKET NOZZLES, *NOZZLE GAS FLOW), WIND TUNNEL MODELS, CONICAL NOZZLES, UNCONVENTIONAL NOZZLES, NOZZLE AREA RATIO, JET MIXING FLOW, THRUST, ANGLE OF ATTACK

Subject Categories : Fluid Mechanics
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE