CORRELATION FORMULAS FOR LAMINAR SHOCK TUBE BOUNDARY LAYER.

Abstract

The laminar boundary layer behind a moving shock is studied. The major objective is to obtain improved correlation formulas (valid for large W, where W is the density ratio across the shock) and to simplify the procedure for obtaining boundary layer parameters. Numerical solutions for shear, heat transfer, and boundary layer thicknesses are presented for 1 < W < infinity, Prandtl Number = 0.67, 0.72 and 1.0 assuming constant rho mu rho = density and mu = viscosity and an ideal gas. Correlation formulas are obtained which agree with these numerical results to within fractions of a percent. Approximate corrections for variable rho mu and real gas effects are then introduced. Charts and tables are presented which describe boundary layers in air (Ms < or = 22) and argon (Ms < or = 10). (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1965
Accession Number
AD0478344

Entities

People

  • H. Mirels

Organizations

  • The Aerospace Corporation

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Fluid Mechanics
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Prandtl Number
  • Shock Tubes
  • Thickness
  • Tubes
  • Viscosity

Fields of Study

  • Physics

Readers

  • Analytical Mechanics
  • Fluid Dynamics.
  • Regression Analysis.