Accession Number : AD0815444

Title :   THE EFFECT OF ROCKET NOZZLE GEOMETRY AND SECONDARY FLOW FIELD ON BASE DRAG AT MACH NUMBERS 2.50 AND 3.00, AN EXPERIMENTAL INVESTIGATION.

Descriptive Note : Memorandum rept.,

Corporate Author : ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s) : Huerta, Joseph

Report Date : MAR 1967

Pagination or Media Count : 48

Abstract : The purpose of this program was to investigate the effect of nozzle geometry and the secondary flow field created by the fin shroud on the model base drag. Wind tunnel tests were performed, utilizing a model with an ogival nose and cylindrical afterbody. The effect of sonic and supersonic-type rocket sustainer nozzles on base pressure was investigated. Also, various fin-shroud configurations were used on these tests in combination with a preselected nozzle. The test Mach numbers were 2.50 and 3.00. All tests were performed with the model at zero angle of attack. (Author)

Descriptors :   (*ROCKET NOZZLES, SECONDARY FLOW), (*SHROUD RINGS, BASE FLOW), AERODYNAMIC CONFIGURATIONS, DRAG, WIND TUNNEL MODELS, FLOW FIELDS, ANGLE OF ATTACK, CYLINDRICAL BODIES, OGIVES, AFTERBODIES, NOZZLE GAS FLOW, INSTRUMENTATION, SUPERSONIC FLOW, GEOMETRY.

Subject Categories : Fluid Mechanics
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE