PRESENTATION OF TEMPERATURE DATA FROM THE HOT ROCKET JET EFFECTS TEST IN THE NACA LEWIS FLIGHT PROPULSION LABORATORY 8 FEET BY 6 FEET WIND TUNNEL,

Abstract

Because reliable methods of predicting conditions in the base region of multiple-rocket-powered missiles are non-existent, a wind tunnel test, with a model including hot rockets, was proposed. The main objective of the test was to compare various sustainer turbine exhaust configurations proposed for use on the three-engine missile. Temperature data have been grouped in Table I in a manner which facilitates comparision of the sustainer turbine exhaust configurations.

Document Details

Document Type
Technical Report
Publication Date
Aug 18, 1958
Accession Number
AD0829823

Entities

People

  • E. E. Frost

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Buildings And Structures
  • Research Facilities
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Theoretical Analysis.