Supersonic Combustion Apparatus

Abstract

An apparatus to study the performance of supersonic combustion chambers was designed, constructed and checked out. However, the main airflow heater (which was supposed to be available for use in this program) was not capable of operating at the combustor design specifications. Therefore, the tests to check out the equipment had to be made with lower air mass flows. Results of preliminary tests in a constant area combustor with hydrogen fuel are reported.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1972
Accession Number
AD0900610

Entities

People

  • Rudolph Edse
  • William A. Strauss

Organizations

  • Ohio State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Flow
  • Air Masses
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Combustors
  • Electric Generators
  • Engineering
  • Exhaust Gases
  • Flow Rate
  • Flowmeters
  • Fuel Injectors
  • Gases
  • Heat Transfer
  • Ignition Lag
  • Supersonic Combustion
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Fluid Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow