脱体涡流型翼面非定常气动力计算方法

本文研究了细长三角翼在脱体涡流型时变攻角所产生的非定常气动力的机理,并采用了一种时间历程的,考虑翼面前、后缘涡面随局部气流拖出并由时间发展逐步形成的数值方法,称之为涡面生成法,计算结果表明该方法是稳定和有效的。

A Numerical Method of Unsteady Separating Flow over Delta Wings

The main purpose of this paper is to explore the developing process of the unsteady separating flow over a Delta wing when its angle of attack suddenly changed, and to extablish a new numerical method to calculate the unsteady flow parameters and aerodynamic forces.After the angle of attack changed, the strength, shape and position of the leading-edge vortex sheet are continuously changed in addition to the shedding and roll up of the wake. It becomes more complicated to calculate the unsteady separating flow than the attached flow. A numerical method considering the time history of the developing process of the leading-edge and trailing-edge vortex sheets has been presented in this paper, it is called the vortex generating method (VGM method).The calculation results show the stability and efficiency of this method, and it will be helpful to the study on the unsteady aerodynamic forces of the wing with leading-edge separating vortices in unsteady motion.