An Experimental and Analytic Investigation of a Transonic Shock-wave/ Boundary-layer Interaction

Abstract

Two wind tunnel tests were conducted in a flow exhibiting a shock- wave/boundary-layer interaction of the type occurring on airfoils at transonic velocities. Boundary-layer pressure distributions were measured with pitot and static probes. Velocities in the free stream and in the boundary layer were obtained with a laser velocimeter (LV) system, and a data reduction program for the LV results was developed. Measurements from the pressure probes and from the LV system are compared with each other and with theoretical computations. It was found that the analytic models for boundary-layer velocity profile and Reynolds stress agree well with experimental measurements.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1977
Accession Number
ADA040023

Entities

People

  • M. C. Altstatt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Data Reduction
  • Flow
  • Fluid Flow
  • Free Stream
  • Laser Velocimeters
  • Layers
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Transonic Flow
  • Velocimeters
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy