A new wing concept which lowers the inviscid drag of a wing in supersonic flow is described. The thrust-wing concept uses a secondary shock that occurs to the rear of the maximum thickness location to produce a significant aerodynamic thrust force from the rearward portion of the wing, thus reducing the inviscid drag. The evaluation of the thrust-wing concept is conducted on a delta-wing planform of differing sweep angles and thicknesses at Mach 1.60 over a wide range of lifting conditions.
Shock-dependent, thrust wings for supersonic flow
AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States
1993-01-01
Conference paper
No indication
English
Shock-dependent, thrust wings for supersonic flow
AIAA | 1993
|Shock-Dependent, Optimum Thrust Wings in Supersonic Flow
NTIS | 1992
|