PRESSURE MEASUREMENTS FOR MACH 8 FLOWS OVER EXPANSION CORNERS AND RAMPS ON AN INTERNALLY COOLED MODEL. PART I. EXPANSION CORNER FLOWS. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS

Abstract

Pressure distributions were obtained for Mach 8 flows over a sharp 40 degree expansion corner and ahead of ramps on an internally cooled model. Full and partial span ramps, having wedge angles up to 30 degrees, were tested at model angles of attack from -45 to +10 degrees for Reynolds numbers ranging from 1.1 to 3.3 million. The model wall temperature was maintained at fairly constant levels ranging from 450 to 1150 degrees Rankine.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1963
Accession Number
AD0431280

Entities

People

  • Louis G. Kaufman Ii.

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Dynamic Pressure
  • Engineering
  • Exhaust Fairings
  • Experimental Data
  • Fairings
  • Flow Rate
  • Flow Separation
  • Heat Energy
  • Heat Transfer
  • Hypersonic Flow
  • Instrumentation
  • Pressure Distribution
  • Pressure Measurement
  • Shock Tunnels
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow