Estimates of Turbulent Boundary Layer Behind a Shock Wave Moving with Uniform Velocity.

Abstract

A theory, previously presented by the author, concerning turbulent boundary-layer development behind a shock moving with uniform speed is briefly reviewed. Numerical results for boundary-layer properties are presented for shock propagation in air at Mach numbers in the range 1.01 < or = M sub S < or = 20. The heat transfer results are in good agreement with the shock tube wall heat transfer measurements of Hartunian et al., which were made in the range 3 < or = M sub S < = 8. Approximate analytical expressions for turbulent boundary-layer properties are deduced, and estimates of the wall temperature variation with distance behind the shock (assumed small) are given. Effects of blowing (wall ablation) are also estimated. The need for experimental data to confirm large Mach number and blowing effects predictions is also noted. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 08, 1977
Accession Number
ADA048445

Entities

People

  • Harold Mirels

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Counter WMD
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Chemical Reactions
  • Equations
  • Experimental Data
  • Free Stream
  • Heat Transfer
  • Layers
  • Mach Number
  • Materials
  • Materials Science
  • Physics
  • Physics Laboratories
  • Shock Tubes
  • Surface Temperature
  • Test And Evaluation
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.