旋转翼-身-尾组合体非对称涡效应的数值模拟与计算

Numerical Simulation and Calculation of the Effect of Asymmetric Vortices for Spinning WingBodyTail Combination

研究了旋转弹在超音速大攻角下，非对称涡的产生、发展以及气动力和力矩的数值模拟算法．以Ｆ．Ａ．Ｗｏｏｄｗａｒｄ等人的有限基本解方法为基础，计及了旋转对弹体脱落涡、弹翼前缘涡、侧缘涡和后缘涡等诸涡系生成、发展的影响．计算结果表明，所提出的方法反应了旋转飞行器超音速、大攻角的气动特性．

The numerical simulation of spinning vehicle in supersonic flow at high angles of attack was studied.The method was based on finite elementary solution put forward by F.A.Woodward and took into account the effects of spinning on vortices shed from body and all kind of vortices shed from wing.All of results indicated that the principal features of the flow phenomena were modeled correctly.