Transonic Wind Tunnel Investigation of Thrust Effects on Missile Aerodynamics.

Abstract

Transonic wind tunnel tests were conducted on an Army Missile Command (AMC) base drag research missile model in the Calspan Corporation 8-Foot Transonic Wind Tunnel during January of 1973. These tests were conducted in order to determine the effect of jet plumes on the stability characteristics of fin and ringtail afterbody confugurations. Afterbody forces and moments and base pressure were measured at jet thrust levels from zero to 400 pounds. The tests were conducted at Mach numbers from zero to 1.25 and at angles of attack from -5 to +10 degrees. The report presents details of the test program, an outline of the test procedures, and results of the investigation in tabular form.

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1973
Accession Number
AD0762576

Entities

People

  • R. J. Dennis

Organizations

  • Calspan

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamics
  • Afterbodies
  • Base Pressure
  • Corporations
  • Mach Number
  • Transonic Wind Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Technical Research and Report Writing.