A wing structure for a supersonic aircraft including a pair of supersonic wave-tripping channels formed on each of two laterally extending wings of the supersonic aircraft, wherein each of the pair of supersonic wave-tripping channels extend in a span-wise direction of the wings respectively, wherein an upper supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on an upper surface of each of the wings and a lower supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on a lower surface of each of the wings, wherein the upper supersonic wave-tripping channel and the lower supersonic wave-tripping channel are set back from a leading edge of the wings respectively.
AIRFOIL FOR SUPERSONIC AIRCRAFT
TRAGFLÜGEL FUER UEBERSCHALLFLUGZEUG
PROFILÉ AÉRODYNAMIQUE POUR AVION SUPERSONIQUE
2024-05-08
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Supersonic airfoil optimization
AIAA | 1987
|Supersonic airfoil optimization
NTRS | 1987
|Supersonic airfoil optimization
AIAA | 1986
|Airfoil theory at supersonic speed
TIBKAT | 1939
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