The progress of two studies which apply nonlinear aerodynamics to supersonic wing design is reviewed. The first study employed a nonlinear potential flow code to design wings for high lift and low drag due to lift by employing a controlled leading-edge expansion in which the crossflow accelerates to supercritical conditions and decelerates through a weak shock. The second study utilized a modified linearized theory code to explore the concept of using 'attainable' leading-edge thrust as a guide for selecting a wing leading-edge shape (planform and radius) for maintaining attached flow and maximizing leading-edge thrust. Experimental and theoretical results obtained during the course of these two studies are discussed.
An overview of two nonlinear supersonic wing design studies
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV
1983-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch