The invention discloses a method for reducing heat and drag of a hypersonic aircraft, which comprises the following steps: generating a wall surface normal cold jet flow and/or a wall surface tangential cold jet flow on the wall surface of the hypersonic aircraft, so that a layer of surface cold air film is formed on the boundary layer of the surface of the hypersonic aircraft under the interaction of the cold jet flow and incoming flow. The method is applied to the field of aircraft design, an original gas-solid shearing layer on the surface of the hypersonic aircraft is changed into a gas-gas shearing layer through the surface cold air film generated through interaction of the cold jet flow and the incoming flow, and the speed shearing gradient and the temperature gradient of fluid near the wall face of the hypersonic aircraft are reduced; therefore, the friction resistance and the heat flux density of the boundary layer are reduced, and the heat and resistance reduction of the hypersonic aircraft can be realized with low cost, long time and high efficiency.
本发明公开了一种高超声速飞行器降热减阻方法,通过在高超声速飞行器壁面上生成壁面法向冷射流和/或壁面切向冷射流,使得冷射流与来流的相互作用下在高超声速飞行器表面边界层形成一层表面冷气膜。本发明应用于飞行器设计领域,通过冷射流与来流的相互作用生成的表面冷气膜将高超声速飞行器表面原来的气‑固剪切层变成气‑气剪切层,减小了高超声速飞行器壁面附近流体的速度剪切梯度与温度梯度,进而实现边界层摩擦阻力与热流密度的降低,能够低成本、长时间、高效率的实现对高超声速飞行器的降热减阻。
Heat reduction and resistance reduction method for hypersonic flight vehicle
一种高超声速飞行器降热减阻方法
2022-11-25
Patent
Elektronische Ressource
Chinesisch
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