A PRELIMINARY ANALYSIS OF ROCKET EXHAUST JET EFFECTS ON MISSILE SKIN AND BASE PRESSURES AT MACH 0.6 AND 1.5 - NACA LEWIS FLIGHT PROPULSION LABORATORY TEST 2093,

Abstract

A wind tunnel test of a one-thirtieth scale 'B' series Atlas missile with operating rocket engines was run at the NACA Lewis 8-by-6 foot supersonic wind tunnel. The primary test objective was to determine the amount of rocket and gas turbine exhaust recirculation into the missile base region; a secondary objective was to determine the effect of operating rockets on missile skin and base pressure. Only the pressure data are considered in this report. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 19, 1958
Accession Number
AD0829820

Entities

People

  • G. E. Powell

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Pressure
  • Engines
  • Gas Turbines
  • Laboratory Tests
  • Rocket Engines
  • Rocket Exhaust
  • Rockets
  • Supersonic Wind Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Missile Defense Systems.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow