PRESSURE AND HEAT TRANSFER MEASUREMENTS FOR HYPERSONIC FLOWS OVER EXPANSION CORNERS AND AHEAD OF RAMPS. PART 3: MACH 8 PRESSURE DATA FOR FLOWS AHEAD OF RAMPS PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS

Abstract

Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for Mach 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for Mach 8 for Reynolds numbers between 1.1 and 3.3 million.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1963
Accession Number
AD0431202

Entities

People

  • Louis G. Kaufman Ii.

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Aerodynamic Control Surfaces
  • Air Force
  • Engineering
  • Flat Plate Models
  • Flow Separation
  • Heat Transfer
  • Hypersonic Flow
  • Measurement
  • Models
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Tunnels
  • Systems Engineering
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow