PRESSURE MEASUREMENTS FOR MACH 8 FLOWS OVER EXPANSION CORNERS AND RAMPS ON AN INTERNALLY COOLED MODEL. PART II. FLOWS OVER A FLAT PLATE WITH AND WITHOUT A PARTIAL SPAN RAMP. 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, 1964
Accession Number
AD0609458

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
  • Flight
  • Flow Separation
  • Heat Energy
  • Heat Transfer
  • Hypersonic Flow
  • Instrumentation
  • Leading Edges
  • Pressure Distribution
  • Pressure Measurement
  • Shock Tunnels
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mechanical Engineering/Mechanics of Materials.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow