Effects of Wind Tunnel Disturbances on Boundary-Layer Transition with Emphasis on Radiated Noise: A Review

Abstract

Effects of wind tunnel free-stream disturbances on boundary-layer transition are reviewed. Experimental results show that free-stream disturbances dominate the transition process as determined by the experimentally measured transition Reynolds numbers on simple geometries (flat plates and sharp cones). Principal modes of disturbance are turbulence (u(tilde)/U infinity) and acoustic sound (p(tilde)/q infinity) at subsonic speeds; hole/slot acoustic resonance at transonic speeds (p(tilde)/q infinity); and tunnel wall turbulent-boundary layer radiated noise at supersonic-hypersonic speeds (p(tilde)/q infinity). Data correlations and resulting empirical equations that show the direct relationship between transition Reynolds numbers and free-stream disturbance levels are presented and discussed.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1980
Accession Number
ADA384962

Entities

People

  • Samuel R. Pate

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Boundary Layer Control
  • Computational Fluid Dynamics
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Hydrodynamics
  • Jet Propulsion
  • Reynolds Number
  • Standing Waves
  • Test And Evaluation
  • Test Facilities
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Acoustical Oceanography.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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