Velocity Measurements in a 3D (Three Dimensional) Shock Wave Laminar Boundary Layer Interaction.

Abstract

An experimental investigation of the three dimensional laminar boundary layer separation associated with an incident swept shock wave was conducted in the von Karman Institute (VKI) S-1 supersonic wind tunnel operating at Mach 2.15. Mean velocity profiles were measured both in the attached separated and reattachment flow regions using a laser doppler velocimeter. A comparison of the measurements with a full 3D Navier-Stokes solver, developed at the VKI, exhibited good agreement in all three regions, thus validating the code which was based on the Beam-Warming algorithm. The report also reviews the earlier parts of the grant dealing with the necessary developments in LDV to achieve high quality data, and the of the 2D shock boundary layer interaction. Keywords: Two dimensional flow; Three dimensional flow; Laminar boundary layer; Flow separation.

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Document Details

Document Type
Technical Report
Publication Date
Jul 31, 1987
Accession Number
ADA187334

Entities

People

  • G. Degrez
  • J. J. Ginoux

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Algorithms
  • Boundaries
  • Boundary Layer
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Mechanics
  • Pressure Distribution
  • Shock Waves
  • Three Dimensional
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow