In order to suppress aeroelastic instabilities on a transonically operating aircraft comprising a pair of wing halves at which a transonic flow forms spatially limited supersonic flow regions that each, in a main flow direction of the flow, end in a compression shock, a boundary layer of the flow is temporarily thickened-up in at least one supersonic flow region at at least one of the two wing halves, when approaching a flight envelope of the aircraft with increasing flight Mach number of the aircraft. The boundary layer of the flow is thickened-up to such an extent that the compression shock at the end of the respective supersonic flow region at the present flight Mach number of the aircraft induces a separation of the boundary layer of the flow from the wing half.
Method of and transonically operating aircraft having devices for suppressing aeroelastic instabilities
2025-02-18
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2022
|Design of a transonically profiled wing
NTRS | 1978
|Design of a Transonically Profiled Wing
NTIS | 1978
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Engineering Index Backfile | 1963
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