论文部分内容阅读
本文给出了绕弯曲头锥理想气体超音速流动差分数值计算方法。这是一个三维绕流问题,由于弯曲头锥的外形特点,头锥部分的数值计算采用了计算轴移动法。数值计算采用MacCormack二阶精度二步格式,物面上用一组由特征相容条件导得的方程。本方法已经用BCY算法语言编制成计算程序,在109丙电子计算机上进行运算。本文最后给出计算实例。
In this paper, a method to calculate the difference of supersonic flow around the curved cone of ideal gas is given. This is a three-dimensional flow around the problem, due to the shape of the curved nose cone, the first part of the calculation of the numerical method of calculating the axial movement axis. The numerical calculation uses the MacCormack second-order precision two-step format, and the object surface uses a set of equations derived from characteristic compatible conditions. This method has been compiled into a calculation program using the BCY algorithm language and calculated on a 109C computer. At the end of this paper, a calculation example is given.