Accession Number:

ADA024346

Title:

Subsonic Two-Dimensional Wind Tunnel Investigations of the High Lift Capability of Circulation Control Wing Sections

Descriptive Note:

Final rept. May 72-Mar 75

Corporate Author:

DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT

Personal Author(s):

Report Date:

1975-04-01

Pagination or Media Count:

117.0

Abstract:

Two series of Circulation Control Wing airfoil sections, formed by the conversion of the sharp trailing edge into a circular bluff surface with tangential upper surface blowing, were evaluated subsonically to determine their high lift characteristics as potential STOL wing sections. Parameters investigated which had noticeable effect on the blown airfoil performance include leading edge devices type of device and degree of deflection, trailing edge configuration radius, slot location, deflection, etc., Reynolds number, airfoil incidence, momentum coefficient, slot height, and nozzle pressure ratio. Maximum lift coefficients roughly triple those of the flapped conventional sections were generated at incidence slightly less than the conventional stall angles and at blowing rates obtainable from bleed of state-of-the-art turbojet engines. An experimental investigation into the lift augmenting effects of pulsed unsteady blowing was conducted on a smaller radius trailing edge configuration. An additional investigation was conducted to determine the effects of spoilers or similar disturbances ahead of the jet exit. The results of the above investigations provide a data base for the prediction of the aerodynamic characteristics of aircraft employing Circulation Control trailing edges to increase their STOL capability. Author

Subject Categories:

  • Aerodynamics
  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE