Aeroelastic instability attenuation method in transonic operating airplanes and airplanes equipped with devices for implementing the method by direct intervention in the aerodynamic boundary layer

摘要

For the attenuation of aeroelastic instabilities in a transonic operating aircraft (10) which has a pair of wing halves (6) at which transonic flow forms spatially limited supersonic flow zones (7) resulting respectively in a compressive shock (8) in the main direction of flow, a boundary layer (15) of the flow is temporarily thickened in such a way, when approaching a flight envelope (1) with increasing in-flight Mach speed of the airplane (10), in at least one of the supersonic flow zones (7) at the level of at least one of the two wing halves (6), that it is ensured that the compression shock (8) resulting in the respective supersonic flow zone (7) causes the boundary layer (15) to peel off the wing half (6) at the aircraft's current in-flight Mach speed (10). Figure for the abstract: Fig. 6