An Experimental Study into the Scaling of an Unswept-Sharp-Fin-Generated Shock/Turbulent Boundary Layer Interaction.

Abstract

An experimental study was carried out of the three-dimensional shock wave/turbulent boundary layer flow-field generated by sharp fin with an unswept leading edge at a 10 deg angle-of-attack to the incoming flow. The model was mounted on and normal to either the tunnel floor or a horizontal flat plate. Both tests surfaces generated a fully developed, equillibrium tubulent boundary layer, with incoming thicknesses of 1.29 cm. and .45 cm., respectively. The incoming freestream was at a nominal Mach number of 2.95 and a Reynolds number of 6.3 x 10 to the 7th power/meter. All surfaces were near adiabatic wall temperature. The three objectives of this study were to learn more about the structure of this type of interaction, to examine the scaling of the resulting flow-field, and to obtain a detailed data set with which to compare numerical computations. The results show that the scaling of this type of interaction is dependent upon both local boundary layer thickness and freestream Reynold number.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1983
Accession Number
ADA126919

Entities

People

  • William B. Mcclure

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Boundary Layer
  • Computational Fluid Dynamics
  • Data Sets
  • Flow
  • Flow Fields
  • Geometry
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Waves
  • Three Dimensional
  • Turbulent Boundary Layer
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.