A flow control device used for suppressing the interference intensity of a shock wave boundary layer is installed in an interference area of a shock wave turbulence boundary layer on the surface of an aircraft and is a control array composed of a plurality of passive control units with curvature profiles, and the passive control units are evenly arranged on the surface of the aircraft in the spanwise direction. The front edge curvature profile of each passive control unit is tangent to the surface of the aircraft, and the rear edge curvature profile is higher than the surface of the aircraft, so that a step is formed on the rear edge. After incoming flow passes through the control unit, the incoming flow is gradually compressed due to the action of the curvature profile of the unit, and the wall surface pressure rises gently compared with a discontinuous object surface without the control unit, so that local flow separation and generation of reattached shock waves are avoided, the interference intensity of a shock wave boundary layer is effectively inhibited, and the service life of the device is prolonged. And a high heat flow peak value caused by shock wave/turbulence boundary layer interference is reduced.
一种用于抑制激波边界层干扰强度的流动控制装置,安装在飞行器表面激波湍流边界层干扰区内部,为由多个具有曲率型面的被动控制单元构成的控制阵列,多个被动控制单元沿展向均匀设置在飞行器表面;单个被动控制单元前缘曲率型面与飞行器表面相切,后缘曲率型面高出飞行器表面,从而在后缘形成台阶。来流经过控制单元后,由于单元的曲率型面的作用而被逐渐压缩,相比未布放控制单元的间断物面,壁面压力上升平缓,从而避免了当地的流动分离及再附激波的生成,有效抑制了激波边界层干扰的强度,减小了激波/湍流边界层干扰导致的高热流峰值。
Flow control device for suppressing interference intensity of shock wave boundary layer
一种抑制激波边界层干扰强度的流动控制装置
23.05.2023
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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