Reynolds Number Effects on the Shock Wave-Turbulent Boundary Layer Interaction at Transonic Speeds.

Abstract

A Ludwieg tube experiment is described in which the pertinent features of the shock wave-boundary layer interaction on an airfoil are simulated with a two-dimensional flat plate in a supersonic nozzle. The nozzle is modified to impress an airfoil pressure distribution on the flat plate that is typical of a cruising flight condition. A normal shock wave is positioned at a fixed location on the plate, and measurements are made in the vicinity of the shock wave-boundary layer interaction zone.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1973
Accession Number
ADA040286

Entities

People

  • B. H. Sheen
  • C. E. Wittliff
  • P. A. Catlin
  • R. J. Vidal

Organizations

  • Calspan

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Flow Fields
  • Fluid Dynamics
  • Hydrodynamics
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Shock Tubes
  • Shock Waves
  • Skin Friction
  • Static Pressure
  • Test Facilities
  • Turbulent Boundary Layer
  • Two Dimensional
  • Waves
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow