Drag reduction systems and methods for an aircraft include a first vortex generator position on a portion of the aircraft, and a second vortex generator positioned on the portion of the aircraft. The first vortex generator is associated with the second vortex generator. The first vortex generator is asymmetrical to the second vortex generator in relation to a coupling axis in order to offset the longitudinal contribution of the vortex generator to vehicle cross-sectional area.
Drag reduction systems for aircraft
2021-04-20
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Supersonic aircraft drag reduction
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