Unsteady Flow Past a Pitching Airfoil at Moderately High Subsonic Free Stream Mach Numbers

Abstract

An experimental and computational investigation was carried out to study the flow past a NACA 0012 airfoil undergoing pitch up motion at free Mach numbers ranging 0.3 to 0.8. The flow velocity field was captured using PIV demonstrating the ability of the technique to characterize high speed separated flows. A companion computational study was conducted to assess the effect of wind tunnel walls on the dynamic stall process....NACA 0012, Airfoil, Flow Velocity.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1992
Accession Number
ADA260118

Entities

People

  • A. Krothapalli
  • G. Buzyna
  • L. Lourenco

Organizations

  • Florida A&M University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Grids
  • Measurement
  • Mechanical Properties
  • Particle Image Velocimetry
  • Physics Laboratories
  • Reynolds Number
  • Stratified Fluids
  • Three Dimensional
  • Turbulent Mixing
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)