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介绍用于近似计算绕三维尖体无粘流激波薄层的二层模型。本法以数值确定激波的位置，在计算不同结构形状物体的空气动力特性时能确定气体动力载荷的近似值。采用这种方法实际上排除了超高速理论中其他已知方法对尖体几何形状所加的约束。与通常的空气动力特性曲线相结合，此法可获得在设计和非设计飞行状态下飞行器整个系统的近似绕流流场，且可优化其空气动力结构。
This paper introduces a two-layer model for approximate calculation of a thin layer of non-stick-flow shock around a three-dimensional tip. This law determines the location of shocks numerically to determine the approximate aerodynamic load when calculating the aerodynamic characteristics of objects of different shapes and shapes. The use of this method virtually eliminates the constraints imposed on the geometry of the tip by other known methods in hypervelocity theory. In combination with the usual aerodynamic characteristics, this method yields an approximate flow field around the entire system of the aircraft under design and non-design flight conditions and optimizes its aerodynamic structure.