A Three-Dimensional Study of Fin-Induced Shock Wave Turbulent Boundary Layer Interaction.

Abstract

Surface pressure distributions and oil streak patterns have been measured in the three-dimensional flowfield caused by the interaction of a skewed shock wave with a two-dimensional turbulent boundary layer. The boundary layer was developing on a 45 deg sweptback, sharp leading edged plate. Tests were made at a freestream Mach number of 2.95, a freestream unit Reynolds number of 63,000,000/m (1,600,000/in), a stagnation temperature of about 265 K and at near adiabatic wall temperature. Measurements have been made for generator angles in the range 0 to 12 deg in 2 deg increments. These measurements represent the first phase of a study which will include heat transfer measurements and details of the flowfield. The measured data are presented and compared with data obtained under the same shock wave conditions but with a different boundary layer. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 15, 1977
Accession Number
ADA049772

Entities

People

  • C. D. Cosad
  • D. S. Dolling
  • I. E. Vas
  • S. M. Bogdonoff

Organizations

  • Princeton University

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Flow
  • Flow Fields
  • Heat Transfer
  • Layers
  • Leading Edges
  • Mach Number
  • Measurement
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Waves
  • Stagnation Temperature
  • Static Pressure
  • Three Dimensional
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.