INCOMPRESSIBLE FLOW PAST A FLAT PLATE AEROFOIL WITH LEADING EDGE SEPARATION BUBBLE

A simple flow model has been developed to predict the size of the separation bubble which forms at the sharp leading edge of a flat plate aerofoil at incidence alpha which are less than about 8 degrees, and the corresponding lift and drag coefficients. This flow model is based on irrotational flow and source singularities which are determined indirectly from experiment. The bubble length is shown to be proportional to alpha 2 with a slope which depends on the rate of growth of the separated shear layer. A thin double-wedge aerofoil has been tested in a wind tunnel. It is concluded that these and previous measurements agree fairly well with the theory for chord Reynolds numbers greater than about 0.5x106.

  • Supplemental Notes:
    • Aeronautical J, v 96 n 952, Feb 1992, p 57 [8 p, 33 ref, 10 fig]
  • Authors:
    • Newman, B G
    • Tse, M C
  • Publication Date: 1992

Language

  • English

Subject/Index Terms

Filing Info

  • Accession Number: 00716245
  • Record Type: Publication
  • Source Agency: British Maritime Technology
  • Files: TRIS
  • Created Date: Feb 28 1996 12:00AM