The invention belongs to the field of aircraft design, and relates to an aircraft low-wave-resistance aerodynamic configuration and a design method.The aircraft low-wave-resistance aerodynamic configuration comprises an aircraft body and wings, the aircraft body and the wings are rotating bodies, and the aircraft body comprises a front cone and a rear cone; incoming flow air is compressed for the first time through a first compression cavity on a front cone, the incoming flow air is compressed for the second time after reaching a second compression cavity to form a front edge shock wave surface, and rear incoming flow air forms a machine body expansion wave surface when reaching a rear cone of a pressure reduction cavity, and pressure reduction is conducted under the action of shock wave expansion waves; in this way, the pressure acting on the front cone of the machine body is compressed only once, and the pressure acting on the rear cone of the machine body is compressed twice and decompressed once. Therefore, the pressure acting on the rear cone of the machine body is close to the pressure acting on the front cone of the machine body, namely, the pressure difference between the front cone and the rear cone of the machine body is small, so that the pressure difference between the front cone and the rear cone of the machine body can be obviously reduced, and the shock wave resistance of the pneumatic structure is greatly reduced.
本申请属于飞行器设计领域,为一种飞行器低波阻力气动构型及设计方法,包括机体和机翼,机体和机翼均为旋成体,机体包括前圆锥和后圆锥;来流空气通过前圆锥上的第一压缩腔处进行第一次压缩,来流空气在到达第二压缩腔后进行第二次压缩,形成前沿激波面,而后来流空气在到达减压腔后圆锥处时形成机体膨胀波面,在激波膨胀波的作用下减压;这样作用在机体前圆锥上的压力只经过了一次压缩,而所述作用在机体后圆锥上的压力经过了两次压缩一次减压;因此,作用在所述机体后圆锥上的压力接近于作用在机体前圆锥上的压力,即机体前圆锥和后圆锥的压力差比较小,能够显著降低机体前圆锥和后圆锥的压力差,从而大幅降低气动构型的激波阻力。
Aircraft low-wave-resistance aerodynamic configuration and design method
一种飞行器低波阻力气动构型及设计方法
2023-03-31
Patent
Elektronische Ressource
Chinesisch
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