CALCULATION OF THE LIFT ON AIRFOILS WITH SEPARATED BOUNDARY LAYERS

The report contains a method for calculating the sectional lift coefficient Cl as a function of its angle of attack alpha and free stream Reynolds number Re even at large angles of attack beyond the maximum Cl. The results of the present theory are in agreement with all known experimental data, that is, (1) the theory shows that Cl increases with alpha until stall and then decreases as alpha is increased still further (keeping Re constant), (2) the theory shows that the Reynolds number effect on Cl versus alpha is insignificant at the lower angles of attack but becomes more pronounced near and beyond the stall where viscous effects and flow separation are more important, (3) the theory shows that Cl increases with Re at constant (high) values of alpha.

  • Supplemental Notes:
    • Report on Project Navy V/STOL Aerodynamics.
  • Corporate Authors:

    West Virginia University, Morgantown

    Deptartment of Mechanical and Aerospace Engineering
    ESB Room 151
    Morgantown, WV  USA  26506-6106
  • Authors:
    • Ness, N
    • Gibbs, E H
    • Tseng, W P
  • Publication Date: 1972-5

Media Info

  • Pagination: 108 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00040928
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: TR-31
  • Contract Numbers: N00014-68-A-0512
  • Files: TRIS
  • Created Date: Feb 23 1973 12:00AM