Interference Heating Due to Shock Impingement

Abstract

Investigation of the interference heating phenomenon was conducted at Mach number 8 over a Reynolds number range from 400 thousand to 3.7 million per ft in the hypersonic wind tunnel. Shock generator models consisted of 1.5, 5, 10 and 15 deg wedges; 2.5, 7.5 and 12.5 deg cones; .5 and 2.0 in. diameter hemispheres, and an orbiter-type vehicle. Shock receiver models included sharp and blunt flat plates and a booster vehicle. Both pressure distributions and heat transfer distributions were obtained in the regions of shock impingement. The test program was organized in a building-block approach. A limited number of sharp plate runs were performed with a boundary layer trip to obtain turbulent data for comparison with other experiments.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1972
Accession Number
AD0749946

Entities

People

  • Louis G. Haufman Jr.
  • Michael Urkowitz
  • Richard F. Romanowski
  • Robert A. Haslett

Organizations

  • Grumman

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Trips
  • Engineering
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Laminar Boundary Layer
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Three Dimensional
  • Turbulent Boundary Layer
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • AI & ML
  • AI & ML - Bayesian Inference
  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster