Wind Tunnel Tests of a Trapped Vortex-High Lift Airfoil.

Abstract

Two dimensional low speed wind-tunnel tests have demonstrated the feasibility of employing trapped vortex diffusion on a high lift airfoil configuration. All 11 percent supercritical airfoil was selected as the base contour employing both leading and trailing edge flaps. The leading edge flap was 25 percent chord, drooped 30 degrees with the rear flap, 27 percent chord, deflected 15 degrees and 30 degrees. Trapped vortex cavities, affording boundary layer control with rapid diffusion, are located at each of the flap knees. Because of the high trapped vortex efficiency, blowing requirements are minimal. Section lift coefficients, in excess of 6, were achieved in the test. (Modified author abstract)

Document Details

Document Type
Technical Report
Publication Date
Dec 23, 1972
Accession Number
AD0762077

Entities

People

  • C. H. Haight
  • K. M. Krall

Tags

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Airfoils
  • Boundary Layer
  • Boundary Layer Control
  • Diffusion
  • High Lift
  • Leading Edge Flaps
  • Leading Edges
  • Supercritical Airfoils
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Solar Physics