稀薄气体中高超速圆柱绕流仿真研究  

Numerical simulation of flow around circular cylinder at hypersonic flight in rarefied gas

作　　者：黄海龙[1,2] 

机构地区：[1]哈尔滨工业大学土木学院,哈尔滨150090 [2]北京宇航系统工程研究所,北京100076

出　　处：《哈尔滨商业大学学报（自然科学版）》2013年第4期483-487,507,共6页Journal of Harbin University of Commerce：Natural Sciences Edition

摘　　要：高速尤其是高超音速飞行是航空航天发展的主流方向.目前,70 km以上高超音速飞行器的需求越来越大.当飞行高度达到或超过70 km时,稀薄效应明显,此时连续介质假设失效,传统的连续流体运动方程(NS方程)和相应的CFD方法已经失效.利用连续流体运动方程(NS方程)和直接模拟蒙特卡洛方法(DSMC),对四个典型K n(K n分别为0.001、0.01、0.1和1)下的圆柱绕流进行了计算.分析比较发现,随着K n的增大,流场中的激波间断结构变弱变粗,甚至消失,圆柱后方的分离区也逐渐变小直到消失.High -speed flight, especially Hypersonic flight, is one of the main research di- rections of the development of aerospace and the demand for hypersonic aircraft that the flight attitude is more than 70 km is strongly growing. When the flight attitude is more 70 km, rar- efied gas effects are more obvious and the continuum assumption become invalid. The tradi- tional continuous fluid motion equations and the related CFD methods are no longer applica- ble. In this paper, the flow around a cylinder has been investigated using the continuous flu- id motion equations and the Direct Simulation Monte - Carlo method at four typical Kw. The results were that, with the increase of Kn, the layer of the shock wave in the flow field was weakening and thickening or even disappear and the separation zone behind the cylinder also become gradually smaller and smaller until it disappear.

关 键 词：DSMC 稀薄流 圆柱绕流 

分 类 号：V211.25[航空宇航科学与技术—航空宇航推进理论与工程]