Investigation of Small Surface Protuberances Up-Stream of Turbulent Boundary Layer Separation Produced by a Skewed Shock at Mach 3.

Abstract

Tests were undertaken to determine the effect, if any, of a row of small sub-boundary layer-sized cylinders on a region of three-dimensional turbulent boundary layer separation produced by a skewed shock wave at a Mach number of 3. Surface oil flows and pressures showed no influence of the row of cylinders on the region of separation. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 01, 1976
Accession Number
ADA026526

Entities

People

  • Robert H. Korkegi

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Layers
  • Mach Number
  • Shock
  • Shock Waves
  • Three Dimensional
  • Turbulent Boundary Layer
  • Waves

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.