Experimental Investigation of Drag and Lift of Wings with Blunt Trailing Edges in Compressible Flow.

Drag and lift measurements were performed on two rectangular wings with an aspect ratio of LAMBDA equals 2, with various trailing edges, in the Mach number range from M// infinity equals 0. 5 to 2. 2. Additionally to straight trailing edges (sharp and blunt) various ″broken″ blunt trailing edges also were examined. The best of these reduced the drag remarkably. By splitting up the total drag in its components it was possible to predict the relative magnitude of the components and the optimum trailing edge thickness.