LEADING EDGE SEPARATION ON AN AIRFOIL DURING DYNAMIC STALL.

Abstract

To obtain a better understanding of the leading edge separation mechanism on a wing pitching upward with a constant angular velocity, an unsteady boundary layer calculation is performed. The analysis considers a potential flow about a Joukowsky airfoil, which then forms a basis for the boundary layer calculations. An integral technique which is similar to the Karman-Pohlhausen method is used to determine the viscous flow. The movement of the separation point is calculated for several pitching rates. A comparison with some experimental data was made for both the static and dynamic case. It was determined that the point of boundary layer separation coincides with the formation of a separation bubble for the dynamic cases considered. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1969
Accession Number
AD0701771

Entities

People

  • Stephen A. Patay

Organizations

  • Massachusetts Institute of Technology

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Experimental Data
  • Flow
  • Fluid Flow
  • Integrals
  • Layers
  • Leading Edges
  • Potential Flow
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.