振荡射流控制翼型流动分离的数值模拟  

Numerical simulation of oscillating excitation separation flow control over airfoils

作　　者：程永卓[1] 李宇红[1] 霍福鹏[1] 陈佐一[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《清华大学学报（自然科学版）》2002年第12期1644-1646,1666,共4页Journal of Tsinghua University(Science and Technology)

基　　金：国家"九七三"重点基础研究专项经费资助(G1999022306)

摘　　要：为了研究大攻角下振荡射流控制翼型流动分离的机理,应用基于有限体积法和压力修正的SIMPLEC算法,数值模拟了表面施加振荡射流的翼型分离流动。结果表明振荡射流在给定条件下能够显著改善翼型的气动性能,提高翼型的升力系数,升力增幅高达18%。对振荡射流增升的流动机理分析表明,增升的机理是因为振荡射流产生的小扰动完全改变了翼型在大攻角粘性流动时产生的涡列结构,并且在翼型头部产生了非定常的分离涡。This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil. The finite volume method and the SIMPLEC method were used to simulate the separated flow. The results show that an oscillating excitation adding at the airfoil surface can improve aerodynamic performance and increase airfoil lift by 18% in the given condition, and that the excitation totally changes the separation flow vortex structure over the airfoil at large attack angles and creates an unsteady separation bubble at the airfoil leading edge. 

关 键 词：数值模拟 分离主动控制 振荡射流 计算流体力学 大攻角 翼型 气动性能 空气动力学 

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]