BOUNDARY LAYER TRANSITION ON CONES AND SPHERES AT SUPERSONIC SPEEDS-EFFECTS OF ROUGHNESS AND COOLING,

Abstract

Results of experiments on boundary layer transition as affected by single roughness elements on cones and spheres in supersonic flow are reviewed and analyzed. Results for the cone includes cooling, whereupon it is found that cooling decreases transition roughness size linearly with wall temperature. The sphere was uncooled, however the curvature of the surface had to be taken into account to collapse the data for various sized roughness elements. Relationships are presented which correlate roughness, Mach number, cooling, and body curvature effects on transition. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1967
Accession Number
AD0660131

Entities

People

  • C. B. Blumer
  • E. R. Van Driest

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Collapse
  • Curvature
  • Flow
  • Geometry
  • Layers
  • Mach Number
  • Roughness
  • Supersonic Flow
  • Transitions

Fields of Study

  • Physics

Readers

  • Energy Conservation and Renewable Energy Engineering.
  • Fluid Dynamics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers