Heat Transfer in Shock Wave-Boundary Layer Interaction Regions

Abstract

An investigation of the effect of shock wave-boundary layer interaction on aerodynamic heat-transfer coefficients is reported. A literature survey and empirical expressions for predicting peak heat-transfer coefficients in interaction regions, developed with the use of existing experimental data, are presented.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1968
Accession Number
AD0849532

Entities

People

  • C. F. Markarian

Organizations

  • Naval Air Weapons Station China Lake

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Aircrafts
  • Boundary Layer
  • Coefficients
  • Experimental Data
  • Flow
  • Flow Fields
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Literature Surveys
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Shock Waves
  • Turbulent Flow

Fields of Study

  • Physics

Readers

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