多段翼型缝翼前缘结冰大迎角分离流动数值模拟  

Numerical simulation of separated flow around a multi-element airfoil at high angle of attack with iced slat

作　　者：张恒[1] 李杰[1] 龚志斌[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空学报》2017年第2期51-64,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家"973"计划(2015CB755800);国家自然科学基金(11172240);航空科学基金(2014ZA53002)~~

摘　　要：应用基于SST(Shear-Stress-Transport)湍流模型的IDDES(Improved Delayed Detached Eddy Simulation)方法,对大迎角状态下多段翼型缝翼前缘典型角状冰引起的复杂分离流动进行了数值模拟研究。采用后台阶流动标准算例和干净无冰多段翼型分离流动算例对数值方法的可靠性和适用性进行了验证。缝翼结冰状态下的数值模拟结果表明:来流迎角较大时,前缘角状冰将会导致结构相对稳定的流动分离泡产生,分离泡的非定常尾迹会对主翼前缘附近流场产生较为强烈的干扰,抑制了缝道流动的加速效应,使得缝翼增升效率降低。在失速点附近,由于分离泡回流强度随来流迎角而增长,同时脱落旋涡的输运方向逐渐向远离壁面方向偏移,使得尾迹影响区域范围和强度均有所增加。The improved delayed detached eddy simulation（IDDES）based on the shear-stress-transport（SST）turbulent model is applied in the numerical simulation of complex separated flow caused by a typical horn-like ice on the slat leading edge of a multi-element airfoil under a large angle of attack.The reliability and applicability of the numerical method is verified based on the analysis of the standard example of the separation flow and the example of the clean multi-element airfoil.Results of numerical simulation of the slat in icing condition show that the horn ice on the leading edge will lead to formation of a large scale separation bubble with relatively stable structure at high angle of attack.The unsteady wake of the separation bubble will generate relatively strong interference with the flow field around the leading region of the main wing,resulting in the decline of acceleration effect of the flow from the gap and the decrease of slat lift augmentation efficiency.Near the stall point,as the backflow intensity of separation bubble increases with the angle of attack of the incoming flow and the wake vortex transport direction gradually deviates from the wall surface,the range and intensity of the influence area of the wake are increased.

关 键 词：IDDES方法 多段翼型 结冰 分离流动 湍流 旋涡 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]