Airfoil Stall Prediction with 2-D Wind Tunnel and 3-D Flight Verification

A number of modified nine percent thick airfoils were tested two dimensionally in the Ohio State University 6"x12" (15.2 cm x 30.5 cm) airfoil tunnel at .25 Mach and flight Reynolds numbers. Two dimensional analyses were run on the same airfoils using modified versions of the Lockheed Analysis code. Maximum lift comparisons are made with both the laminar and turbulent separation predictions. Results show good correlation of maximum lift and stall characteristics with the test data. Maximum lift analysis has been carried to three dimensions where comparisons are made with flight test data on several of the airfoils.