The invention provides a shock wave suppression device and an aircraft capable of suitably reducing drag on a airfoil surface. The shock wave suppression device configured to suppress a shock wave generated on an airfoil surface of an airfoil includes a bump cover provided to follow the blade surface and deformable to protrude outward from the airfoil surface; and a switching unit configured to switch the bump cover between a steady state to follow the airfoil surface and a deformed state to protrude outward from the airfoil 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 airfoil surface.
本发明提供一种能适当地减小翼面上的阻力的冲击波抑制装置以及航空器。一种能抑制在翼的翼面上产生的冲击波的冲击波抑制装置,具备:凸块罩,仿形设于所述翼面,并且能以从所述翼面向外侧突出的方式变形;以及变换部,使所述凸块罩在仿形于所述翼面的稳定状态和从所述翼面向外侧突出的变形状态之间变换。所述凸块罩的所述变形状态下的形状为从在所述翼面上流通的流体的流通方向的上游侧到下游侧成为连续面的弯曲形状。
Shock wave suppression device and aircraft
冲击波抑制装置以及航空器
20.08.2021
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
SHOCK WAVE DETECTION SYSTEM, METHOD OF DETECTING SHOCK WAVE AND AIRCRAFT
Europäisches Patentamt | 2024
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Engineering Index Backfile | 1960
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SAE Technical Papers | 1960
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