METHOD FOR SUPPRESSING AEROELASTIC INSTABILITIES ON TRANSONICALLY OPERATING AIRCRAFT, AND AIRCRAFT HAVING DEVICES FOR CARRYING OUT THE METHOD BY DIRECT INTERVENTION INTO THE AERODYNAMIC BOUNDARY LAYER

摘要

To suppress aeroelastic instabilities on a transonically operating aircraft (10) which has a pair of wing halves (6) on which a transonic flow forms spatially delimited supersonic flow areas (7) which each terminate in a main flow direction with a compression shock (8), a boundary layer (15) of the flow in at least one of the supersonic flow areas (7) on at least one of the two wing halves (6) is temporarily thickened when a flight envelope (1) is neared with increasing flight Mach number of the aircraft (10), such that it is ensured that the compression shock (8) that terminates the respective supersonic flow area (7) induces a separation of the boundary layer (15) from the wing half (6) at the present flight Mach number of the aircraft (10).