翼型大攻角状态下表面吸气驻涡增升的数值模拟实验  

THE NUMERICAL SIMULATION OF FLOW AROUND AN AIRFOIL WITH SUCTION AT HIGH ANGLE OF ATTACK

作　　者：李锋[1] 汪翼云[1] 崔尔杰[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《力学学报》1993年第5期632-637,共6页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：用数值模拟方法给出了翼型大攻角状态表面吸气后绕翼型流动的某些新现象并对流场的特性进行了机理性研究,其中包括吸气对翼型背风面分离涡的驻涡增升作用;吸气孔位置对流场的影响;不同吸气强度以及间歇式吸气的增升效应。数值模拟的出发方程为N-S方程,差分格式为Beam-Warming格式。数值实验表明:(1)吸气可有效地提高翼型大攻角状态下的升力;(2)在一定吸气强度下吸气可使翼型背风面上涡的非定常脱落现象消失从而起到驻涡作用;(3)吸气孔位置在翼面的中部附近增升效果较好;(4)在一定范围内吸气强度越强其升力越高;(5)间歇式吸气也可提高平均升力,但引起升力的波动。In this investigation, a new phenomenon of stationary vortex was found and some new dynamic process by means of suction on the airfoil surface was studied by numerical method. The full Navier-Stokes equations were solved by the implicit factorized finite difference algorithm. The results show that: (1) The suction can increase the lift force at high incidence. (2) If suction pressure is strong enough, the unsteady vortex shedding phenomenon can be eliminated and steady flow formed. (3) Near the midchord, the suction can provide a higher lift force for the airfoil. (4) The stronger the suction intensity, the higher lift force the airfoil can obtain. (5) The intermittent suction can also supply larger lift force but fluctuation of lift force is found.

关 键 词：吸气效应 驻涡器 分离流 数值模拟 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]