用全位势方程计算侧滑机翼的跨声速绕流特性

本文对大后掠小展弦比细长机翼，由垂直于机翼纵轴的每一横流截面生成Ｏ型网格，从而形成对机翼流场的Ｈ－Ｏ型网格，用守恒型全位势方程，差分方法和隐式近似因式分解ＡＦ２迭代算法计算侧滑机翼的流场。

Computation of Compressible Flows past the Wing with Sideslip Using Full Potential Equation

A method has been presented for calculating the sideslip flow past slender wings with high sweep,using conservative full potential equation and 'H-O' grid. The 'H-O' grid is created by generating a series of 2- D 'O' meshes around the cross flow sections vertical to the wing axis. Such a grid is suitable especially to handle slender configurations.The full-potential equation is solved by finite-difference method and the iteration scheme of implicit approx imate factorization, proposed by Holst.The flows past the left and right wings are computed alternatively. The flows past the two parts are coupled with each other with the flow information transferred through the symmetric plane of the wing. The computer code can be applied to calculating the transonic flow. This dissertation gives computation results of two wings. The computations show that the present results are in good agreement with the experimental ones.This method are also applied to calculating the sideslip flow past wings with high aspect ratio by using conservative full- potential equation and 'C-H' grid. The computation results are given for two wings. Allthe computations give good results.