The biggest lift drag ratio 3.36 considering viscous effects is obtained at Mach 6 when a proper base conical shock wave angle is chosen.
在设计点附近选取合适的半基准圆锥激波角并考虑粘性影响时，可得到乘波体最大升阻比为3.36；
Since the angle of the shock is a function of the body angle, supersonic aircraft have very sharp noses and leading edges so that the oblique shock wave is produced at as small an angle as possible.
由于冲击的角度是弹体角的一个影响因素，超音速飞机的机头都很尖、机翼前缘也很薄，以使产生的斜激波的角度尽可能地小。
Flow field of shock wave passing by right Angle and wedge is analyzed using numerical method and numerical interference technique combining with experimental interferograms.
使用数值计算方法和数值干涉技术并结合实验干涉图片，分析了激波过拐角绕楔形物体运动的流场。
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