计算跨音速三维机翼非定常载荷的核函数法

 本文给出了在跨音速流动中,计算三维机翼非定常载荷分布的核函数法和计算结果。此方法是基于线化升力面理论,利用在亚、超音速情况下,联系载荷分布与下洗的积分方程的核函数,采用局部线化法来处理跨音速的非定常绕流问题。在计算中引进了线分布的冲波偶极子,并嵌入适当的正冲波边界条件。 我们从统一的超、亚音速核函数表达式出发,对亚音速区数值积分作了新的简便的处理,对于亚、超音速区相互的诱导下洗给出了自己的数值积分过程。我们算了三个例题,和文献上的数值符合较好。

A KERNEL FUNCTION METHOD FOR COMPUTING UNSTEADY LOAD ON THREE-DIMENSIONAL WINGS IN TRANSONIC FLOW

A kernel function method and the results of computing unsteady load on three-dimensional wings in transonic flow are presented in this paper. The method is based on linearized lifting surface theory. Local linearization is used for treatment of unsteady transonic flow about wings. A line doublet which represents the additional lift induced by shock movement is adopted in simulating the presence of a normal shocks and the appropriate shock boundary conditions are embedded.A new method dealing with the subsonic chord wise integration is introduced, and the procedures of numerical integration is simplified greatly. We also present procedures for calculation of downwashes. Both the downwash induced on subsonic region by supersonic region and shock doublet and the downwash induced on supersonic region by subsonic region H are included.Three numerical examples are given. The results are in good agreement with the experiments and data given in the references1]and6]. The present method is feasible as an approximate method dealing with unsteady load on three-dimensional wings in transonic flow. I