Quiet Tunnel Experiments of Shock/Boundary Layer Interactions

Abstract

The effect of freestream noise on the shockwave/turbulent boundary layer interaction on a compression ramp is experimentally examined. The experiments are conducted in a supersonic low-disturbance tunnel under both low-level ("quiet") and high-level ("noisy"/"conventional") freestream noise levels. A large-scale, low-frequency oscillation of the shock, that is comparable to that measured In previous conventional tunnel experiments is observed. The intermittent length of the interaction is comparable to that of previous experiments, but larger than that predicted in numerical simulations. Thus the freestream noise levels do not appear to be the source of the previously reported discrepancies between conventional tunnel experiments and simulations.

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Document Details

Document Type
Technical Report
Publication Date
Mar 03, 2006
Accession Number
ADA456817

Entities

People

  • Ndaona Chokani

Organizations

  • Duke University

Tags

Communities of Interest

  • Energy and Power Technologies
  • Sensors

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Compression
  • Free Stream
  • Frequency
  • Hot Wire
  • Layers
  • Leading Edges
  • Light Sources
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Simulations
  • Stagnation Pressure
  • Static Pressure
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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