摘要
本文采用ＭａｃＣｏｒｍａｃｋ两步显式格式，用空间推进法求解Ｅｕｌｅｒ方程来对有翼飞行器的超声速绕流流场进行数值模拟。应用特征边界条件处理物面边界及装配激波的计算。在翼缘及表面斜率不连续处，采用局部解析处理，提高了算法的可靠性。复杂外形的计算采用分区处理技术，网格由代数形式生成。在大攻角的计算中，通过对横流速度型的修正改善了背风面压力分布特性，解决了推进中断问题，同时模拟出背风面涡。
In this paper, an effective method for calculating super-sonic winged vehicles is developed,The explicit MacCormack schems is used to advance interior points while a characteristic boundary condi-tion treatment is applied at surface and the shock.A local analysis is in-voked at wing edges and surface slope discontinuities,which leads to accu-rate surface pressure values near these locations and adds to the robustnessof the procedure. Meshes are generated algebraically and complex shapesare handled by dividing the computational domain into a number of sim-ple zones.So this method is capable of treating a broad range of con-figurations.By modifying the crossflow velocity profiles for the consid-eration of viscous effects.The leeside surface pressure distributions areimproved considerably.Computational interruption problems caused bynumerical oscillations are solved successfully as a result.
出处
《空气动力学学报》
CSCD
北大核心
1995年第2期159-165,共7页
Acta Aerodynamica Sinica
