Heat Transfer Due to Shock Wave Turbulent Boundary Layer Interactions on High Speed Weapon Systems

Abstract

Three-dimensional shock wave turbulent boundary layer interactions caused by a fin-plate configuration were investigated experimentally and analytically. Wind tunnel tests were conducted at a Mach number of 3.71 and the interactions were studied at near full scale conditions by mounting one of several fins normal to the tunnel sidewall in the naturally turbulent, 6 inches thick sidewall boundary layer. Tests were conducted primarily with a sharp leading edge planar fin, although blunt and blunt swept planar fins were also used. The experimental data were used to develop new analytical and correlation procedures.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
ADA002685

Entities

People

  • K. H. Token

Organizations

  • McDonnell Aircraft Corporation

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Free Stream
  • Geometry
  • Heat Transfer
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Test Facilities
  • Test Methods
  • Three Dimensional
  • Turbulent Boundary Layer
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.