绕侧滑锥体,三维机翼与机身的超音速非线性全位势流计算

本文在Grossman的非守恒全位势方程的方法中,提出以固定网格为基础的头激波安装法,节省计算机时。计算结果与实验和欧拉方程解符合很好,与线化理论结果的比较,显示了线化理论的不足。

NONLINEAR SUPERSONIC POTENTIAL FLOW OVER SIDESLIP CONICAL BODIES DELTA WINGS AND FUSELAGES

The governing equation of supersonic nonlinear full-potential flow past aircraft in the spherical crossflow plane has the salient mathematical features of two-dimensional transonic potential flow. Thus, a marching technique can be developed through the application of the successful Jameson's rotated difference scheme and line relaxation iteration for capture of both bow and embedded shocks.The results obtained by this technique in this paper are presented first for the sideslip conical bodies such as model delta wings of thin-elliptic cones and then for the nonconical bodies such as wings of practical configuration, noncircular sectional fuselages with their canopies, and are compared with available experimental data, Euler's equation solutions, and the results from linearized theories. In numerical calculation has been developed a fixed-mesh nose shock fitting technique, which reduces many mesh points so as to further reduce the computation time.