后缘射流对跨音速翼型激波振荡影响的数值模拟  

The Numerical Simulation of Trailing Edge Jet Effect on Shock Oscillation over Airfoil at Transonic Speed

作　　者：周伟[1] 张正科[1] 屈科[1] 高超[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《弹箭与制导学报》2013年第1期135-137,144,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：重点实验室基金资助

摘　　要：跨音速翼型上激波与附面层相互干扰会导致激波在翼型上前后振荡,从而有可能引起机翼抖振。要对激波振荡进行控制主要应通过改变激波附面层相互作用区域的流动和后缘处尾流的流动来实现。通过数值方法模拟后缘射流对尾流流动的改变以及对跨音速翼型上激波振荡的影响。计算了不同射流速度下相对厚度为18%的双圆弧翼型绕流场,分析了后缘射流对激波振荡及翼型气动特性的影响。结果表明后缘射流对激波振荡有抑制作用,同时对翼型气动特性有一定改进作用。The shock/separated boundary layer interaction on transonic airfoil may result in shock oscillation which in turn may lead to wing buffet. Shock oscillation over transonic airfoil might be controlled by modifying the flow in the shock/boundary layer interaction region and by manipulating the wake flow near airfoil trailing edge. The effects of trailing edge jgt on the airfoil wake flow and on shock oscillations were simulated by numerical methods. The flow around an 18% thick biconvex airfoil with various jet velocities were computed, and the effects on shock oscillation and aerodynamic characteristics were analyzed. It is found that the trailing edge jet will suppress the shock oscillation and improve the aerodynamic characteristics of airfoil.

关 键 词：射流 激波振荡 跨音速 附面层分离 

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]