The invention provides a supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control. The method comprises the following steps: step 1, carrying out numerical simulation on a flow field of a supersonic aircraft to obtain positions of a compression area and an expansion area on the lower surface of an aircraft wing in a supersonic cruise state; 2, arranging two to four air suction ports within the range of 5%-15% of the chordwise direction and 10%-80% of the spanwise direction of the compression area; and 3, arranging two to four air blowing openings in the range of 80%-95% of the chordwise direction and 10%-80% of the spanwise direction of the expansion area. The method has the advantages that the air suction port is formed in the compression area of thelower surface of the aircraft wing, the air blowing port is formed in the expansion area, and the sonic boom intensity observed on the ground can be remarkably reduced through the mutual interferenceeffect between shock waves and expansion waves. Meanwhile, the lift force of the whole aircraft can be increased, and the resistance is reduced, so that the aerodynamic performance of the supersonicaircraft is improved, and the supersonic flight requirement is better met.
本发明提供一种基于吹吸气流动控制的超声速飞机声爆抑制方法,包括以下步骤:步骤1,对超声速飞机的流场进行数值模拟,获得超声速巡航状态下飞机机翼下表面的压缩区域与膨胀区域的位置;步骤2,在压缩区域弦向5%‑15%和展向10%‑80%的范围内,布置两个至四个吸气口;步骤3,在膨胀区域弦向80%‑95%和展向10%‑80%的范围内,布置两个至四个吹气口。优点为:本发明通过在飞机机翼下表面的压缩区域安装吸气口,并在膨胀区域安装吹气口,利用激波和膨胀波之间的相互干扰作用,能够显著降低地面观测到的声爆强度。与此同时能够增加全机升力,减小阻力,从而提高超声速飞机的气动性能,更好地满足超声速飞行需求。
Supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control
一种基于吹吸气流动控制的超声速飞机声爆抑制方法
2021-03-26
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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