A Study of Compressibility Effects on Dynamic Stall of Rapidly Pitching Airfoils

Abstract

Results of recent experimental studies into the effect of compressibility on dynamic stall of oscillating airfoils are reviewed. Stroboscopic schlieren images of the strongly unsteady flow field are presented, showing the development of the dynamic stall vortex. and its progression down the airfoil. The effect of varying free-stream Mach number, and frequency of oscillation of the airfoil are demonstrated, and examples of local supersonic flow are presented including the presence of a shock near the leading edge of the airfoil.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1991
Accession Number
ADA244557

Entities

People

  • Lawrence W. Carr
  • Muguru S. Chandrasekhara

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Compressive Properties
  • Flow
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Leading Edges
  • Mach Number
  • Oscillation
  • Photographs
  • Research Facilities
  • Supersonic Flow
  • Turbulent Mixing
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Control Systems Engineering.
  • Theoretical Analysis.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow