Lift Augmentation on Planar Airfoils in the Transonic Regime - a High Reynolds Number Wind Tunnel Study.
Final rept. 1 Mar 72-31 Aug 73,
GENERAL DYNAMICS SAN DIEGO CA CONVAIR AEROSPACE DIV
Pagination or Media Count:
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
- Fluid Mechanics