超声速进气道与弹体一体化外形研究

Integrative design of supersonic inlet and missile body

通过数值求解N S方程和风洞测力试验,研究了超声速进气道的布局、剖面形状及几何参数对全弹气动力和进气道内流的影响。结果表明:细长旋成体弹身背风面和侧边不宜安放进气道;矩形进气道能够产生涡升力,升阻比明显高于半圆形进气道,而且内部流动接近二维流动,流场畸变及流动损失情况均比半圆形进气道要好;矩形进气道横截面积增加,对升力系数影响不大,但阻力系数增加明显;其高宽比增加,升力系数增大,阻力系数减小。

Through solving N-S equation and doing wind tunnel experiment, the influence of the configuration ,shape and geometry parameter of supersonic inlet on aerodynamic character of missile and internal flow of inlet has been investigated. The investigation shows that the back and the side of the missile body are not suitable for installing inlets. The ratio of lift to drag of the rectangle inlet is higer than that of semicircle inlet, and the internal flow character of rectangle inlet is also good. As the growth of the cross section of the rectangle inlet, the lift coefficient varies little, but the drag coefficient increases dramatically. When the ratio of height to width increases, the lift coefficient aggrandizes, and the drag coefficient diminishes.