Accession Number:

AD0912911

Title:

Lift Augmentation on Planar Airfoils in the Transonic Regime - a High Reynolds Number Wind Tunnel Study.

Descriptive Note:

Final rept. 1 Mar 72-31 Aug 73,

Corporate Author:

GENERAL DYNAMICS SAN DIEGO CA CONVAIR AEROSPACE DIV

Report Date:

1973-09-01

Pagination or Media Count:

113.0

Abstract:

Tests were carried out at Mach numbers of 0.75, 0.80, and 0.85 and a Reynolds number of 30,000,00015 inch chord to determine the relative effectiveness of aft camber, jet flaps, or tangential slot blowing, either separately or in combination, to increase the maximum buffet-free lift coefficient. Aside from the force and moment measurements, airfoil surface pressure distributions were obtained. A finite difference calculation is carried out in one case to determine the angle of attack correction due to wall interference effect for the 20 porosity perforated wall wind tunnel. Author

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE