跨音速翼型上的激波／边界层干扰自适应控制计算  

Computation of Transonic Airfoil Flowwith the Shock Boundary LayerInteraction Adaptively Controlled

作　　者：马侠[1] 蒋金贵 张绵纯[1] 肖林奎[1] 

机构地区：[1]中国科学院力学研究所

出　　处：《应用力学学报》1994年第1期60-65,共6页Chinese Journal of Applied Mechanics

摘　　要：在激波区使用自适应壁对跨音速翼型上的激波／边界层的相互作用（干扰）进行控制，可改变机翼的气动性能。这种被动控制可通过在翼型的激波区开一凹腔，其上覆盖一弹性橡胶膜柔壁来实现。本文给出用Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ（Ｎ－Ｓ）方程数值模拟这一自适应控制翼型的跨音速粘性绕流，提出了一个适用于本特殊情况（物面边界局部地区在求解过程中有变化）的处理办法。并探讨了自适应柔壁对当代跨音速翼型绕流的影响。The performance of transonic airfoils can be changed with the shock boundary layer interactioncontrolled by an adaptive surface in the shock region. This passive control can be realized by making acavity on the airfoil and covering it with an elastic rubber membrane wall. A method which can treatthis special case (with the local surface boundary adaptively changed by the flow field around airfoil)is proposed and a procedure which allows the computation of transonic visecous flow over the adaptiveairfoil using Navier-Stokes equation is described. The influence of the adaptive wall on the flow fieldover a medern transonic airfoil has been investigated.

关 键 词：激波 边界层干扰 翼型 跨音速流动 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]