翼尖开孔吹气流动控制数值模拟研究  

Numerical Simulation of Flow Control over a Fixed Wing with Slotted Tip

作　　者：龚志斌[1] 李杰[1] 张恒[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2015年第4期21-23,28,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(11172240);国家重点基础研究发展计划项目资助(2015CB755800);航空科学基金项目资助(2014ZA53002)

摘　　要：在中等展弦比直机翼上设计了由前缘到翼梢端面的四个环形通气孔。采用点对接网格和面搭接网格技术,基于雷诺平均N-S方法,分别选用S-A湍流模型和SST湍流模型,研究了翼尖开孔吹气对机翼尾涡的影响。计算结果表明,翼尖开孔吹气能够显著地耗散翼尖尾涡。从孔中吹出的气流对来流有明显的阻挡作用,能够相应地减小尾涡内的轴向速度,同时孔的出口附近会产生一对方向相反的涡,能够削弱尾涡区内的旋转效应。与其他翼尖展向吹气流动控制措施相比,翼尖开孔吹气方式具有不需要引气来源,结构简单,易于工程实现等优点,是一种良好的尾涡耗散技术。Four annular slots from leading edge to the tip surface are designed on a fixed wing with middle aspect ratio. Combined with the point- to- point and patched structured grid techniques, RANS methods with S- A and SST turbulence models are employed to investigate the slotted tip effects on wake vortex. Results show that vortex in the rear wake can be significantly dissipated by slotted tip. Air blowing out from the slots can block the flow and reduces the axial velocity in the wake. Counter- rotating vortex pair can be formed at downward of each slot exit, and the rotational effects can be weakened. Compared with other spanwise blowing techniques, the slotted tip in this research features simple structure and easy ap- plication to engineering with no additional air sources, and thus should be a promising vortex dissipation technique.

关 键 词：中等展弦比直机翼 桨尖开孔 雷诺平均方法 尾涡耗散 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]