ProblemA shock wave suppression device (10) and an aircraft (1) capable of suitably reducing drag on a blade surface are provided.Solving MeansA shock wave suppression device (10) is configured to suppress a shock wave generated on a blade surface (3a) of a blade (3), the shock wave suppression device including a bump cover (13) provided to follow the blade surface and deformable to protrude outward from the blade surface, and a displacing unit (14) configured to displace the bump cover between a steady state to follow the blade surface and a deformed state to protrude outward from the blade surface. The bump cover has a curved shape in the deformed state configured to be a continuous surface from an upstream side to a downstream side in a flow direction of a fluid flowing through the blade surface.
SHOCK WAVE SUPPRESSION DEVICE AND AIRCRAFT
STOSSWELLENUNTERDRÜCKUNGSVORRICHTUNG UND FLUGZEUG
DISPOSITIF DE SUPPRESSION D'ONDES DE CHOC ET AÉRONEF
25.08.2021
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
SHOCK WAVE DETECTION SYSTEM, METHOD OF DETECTING SHOCK WAVE AND AIRCRAFT
Europäisches Patentamt | 2024
|Shock wave noise of supersonic aircraft
Engineering Index Backfile | 1960
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SAE Technical Papers | 1960
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