A study has been conducted to explore the use of existing aerodynamic techniques to design a new supersonic cruise wing for an existing fighter wind-tunnel model. In addition to the usual wing design constraints of lift, pitching moment, and minimum drag, a ground rule was imposed that the wing had to fit on the existing fuselage. Experimental wind-tunnel results were obtained for a camber design and a reference flat wing. The flat wing was also fitted with leading-edge flaps which approximate the cruise camber design. The experimental results indicate that significant improvements in supersonic cruise capability can be obtained by a new wing designed using existing supersonic aerodynamic techniques.
Design study results of a supersonic cruise fighter wing
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA
1979-01-01
Conference paper
No indication
English
Design study results of a supersonic cruise fighter wing
AIAA | 1979
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