DEVELOPMENT OF A DOUBLE-OBLIQUE-SHOCK SCRAMJET MODEL IN A SHOCK TUNNEL

Abstract

A double-oblique-shock scramjet model has been developed using the AEDC-VKF 16-in. Shock Tunnel I at a free-stream Mach number of 11. The model was developed as a test bed for the development of instrumentation and hydrogen fuel injection techniques for supersonic combustion experiments to be conducted at the 54-in. test section in the AEDC-VKF Tunnel F. Difficulties were encountered, especially at the entrance to the combustor because of the combined action of separation and the interaction of the second shock from the cowl lip. Considerable effort was expended before these influences were reduced to the point that the flow in the combustor was satisfactory. The results of these development tests are reported here.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1969
Accession Number
AD0692466

Entities

People

  • D. A. Wagner
  • H. K. Smithson
  • I. T. Osgerby

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion
  • Combustors
  • Flow Fields
  • Free Stream
  • Heat Transfer
  • Ignition
  • Ignition Lag
  • Instrumentation
  • Mach Number
  • Pressure Distribution
  • Shock Tunnels
  • Shock Waves
  • Static Pressure
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion science or combustion engineering.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow