Control configured vortex flaps

Details Control configured vortex flaps Control configured vortex flaps

1990-10-19

1992-03-10

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244 90R, B64C 900

Patent

active

050944118

ABSTRACT:
Individually deflectable, segmented, vortex flaps are provided on the leading edges of a delta wing supersonic aircraft to permit selective lateral and directional control moments to be created on the aircraft at high angles of attack, where conventional elevons and rudders have become ineffective. By selectively deflecting the segmented vortex flaps simultaneously in the same direction or differentially, the lateral and directional control of high-swept, thin wing, supersonic speed aircraft, at high angles of attack, is improved.

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