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

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)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1967
Accession Number
AD0815444

Entities

People

  • Joseph Huerta

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Pressure
  • Flow
  • Flow Fields
  • Gas Turbine Nozzles
  • Geometry
  • Mach Number
  • Nozzles
  • Rocket Nozzles
  • Rockets
  • Secondary Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow