【摘要】 从N-S方程出发,推得用于描述飞行器分离涡的可压缩、粘性涡核方程,给出了对于亚、跨、超音速都适用的数值解法,它可以计算分离涡或尾迹涡特性。导出了可压缩分离涡的破裂条件,并用于计算破裂位置。得到和分析了压缩性等参数对分离涡运动影响的一系列感兴趣特性。更多还原

【Abstract】 Based on the Navier-Stokes equations, the compressible viscous vortex equation des-cribing the separated vortex of an aircraft is derived and a numerical method for solving this equation is developed. It can be used to subsonic, transonic and supersonic vortex flows. The breakdown condition of the compressible separated vortex is derived and used to compute the breakdown place. A series of interesting features about the effects of various parameters such as compressibility etc. on separated vortex motion are obtained and analysed.更多还原