二维翼型抽吸气层流控制技术的数值研究  

Numerical investigation of the suction-laminar-flow-control technology on an airfoil

作　　者：段会申[1] 刘沛清[1] 陈建中[1,2] 佟增军[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2010年第6期676-682,共7页Acta Aerodynamica Sinica

基　　金：航空科学基金(08ZA51003)

摘　　要：数值模拟了表面开孔吸气控制下的翼型绕流流场。主要研究了孔径、孔间距、吸气区大小和位置等吸气参数对二维翼型气动性能的影响。计算选用SSTk-ω湍流模型,并对标准的Wilcox转捩模式进行了修正。计算结果表明:修正的转捩模式能较好地模拟表面吸气引起的转捩位置的变化;在不同孔径、孔间距和吸气区位置的吸气控制下,翼型总阻力随吸气系数的增加均呈先减小后增大的变化规律;采用较大的孔径、孔间距以及较小的吸气区域进行吸气控制,具有较大的翼型阻力恢复吸气系数和较低的相对阻力最小值。The flow fields around an airfoil of porous-surface suction were simulated numerically.The emphasis was on the impact of hole diameter,hole spacing,suction area location,suction coefficient,and other suction parameters on aerodynamics performance for an airfoil.The SST k-ω two-equation turbulence model was applied to simulate turbulent and transition flow,and its Wilcox transition model was modified to improve the prediction precision.The results show that corrected transition model is able to better predict the variation of transition position with suction control.Under different porous diameters,spacings,and the sizes and positions of the suction region,the total drag maintains the variation trend of firstly decreasing by up to minimal value,then increasing with the gradual increase of suction coefficient.Adopting the bigger hole diameter,spacing and smaller suction zone to the boundary-layer suction control,the large drag-recovery suction coefficient and the lower relative drag minimum are acquired.

关 键 词：转捩 层流流动 湍流模型 抽吸气控制技术 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] O357.41[理学—流体力学]