翼面吸气混合层流控制的数值研究  

Numerical simulations of hybrid laminar flow control by suction over an airfoil

作　　者：张驰宇[1] 肖志祥[1] 邓一菊[2] 

机构地区：[1]清华大学航天航空学院,北京100084 [2]中国航空工业第一飞机设计研究院,西安710089

出　　处：《中国科学：物理学、力学、天文学》2014年第9期944-954,共11页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家自然科学基金资助项目(批准号:11372159)

摘　　要：本文采用Menter发展的γ-Reθ转捩/湍流模式预测平板和超临界RAE-2822翼型的转捩特性,验证了该转捩模式的有效性和可靠性,同时获得网格分布等规律.在此基础上开展某超临界翼型上表面及其前缘结冰时吸气层流控制后的转捩预测,分别获得干净和结冰外形下混合层流控制对转捩的影响规律.结果表明,合理设计的层流控制对干净翼型表面转捩推迟明显,能有效减阻;在结冰情况下,层流控制几乎失效.In this article, the transition model, γ-Reo, proposed by Menter, was applied to model the transition past a flat plate and a supercritical airfoil, RAE-2822. The computational results show good agreements with the available measurements. It shows that this transition model is effective and reliable to simulate the transition over the airfoil. Furthermore, this transition model is applied to simulate the hybrid laminar flow control by suction past another supercritical airfoil with and without the ice at the leading edge. From the results for the clean airfoil, the laminar flow control is effective and the rational suction can highly delay the flow transition on the upper surface and the skin friction can be effectively reduced. When the airfoil with the ice at the leading edge, all the laminar flow control are out of work. The transition occurs just behind the glaze and blunt rime ice.

关 键 词：转捩模式 吸气 混合层流控制 前缘结冰 

分 类 号：O357.5[理学—流体力学]