增加翼型升力的局部振动流动控制技术  

Vibration Flow Control Technology for Increasing Lift of Airfoil

作　　者：裘进浩[1] 李大伟[1] 聂瑞[1] 季宏丽[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《南京航空航天大学学报》2012年第5期638-644,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(50830201)资助项目;教育部长江学者创新团队(IRT0968)资助项目;江苏省普通高校研究生科研创新计划(CXLX12-0165)资助项目;中央高校基本科研业务费专项资金资助项目

摘　　要：以增加升力、弱化激波为目的,采用计算流体力学的方法,开展了流场主动控制技术的研究。提出了内埋压电材料在上翼面引入周期性正弦振动形成附面层扰动这一主动控制方法。利用结构网格和相应的非定常流计算方法,对变形过程中的气动特性进行了数值仿真。分析了各种变形参数对升力特性的影响。以往的研究大多局限在二维翼型的数值仿真,本文将计算方法扩展到三维机翼模型,以进一步验证控制方法的有效性。研究表明,通过适当的参数优化,局部主动变形能够改善翼型背风区的气动特性,起到增升减阻的作用。低马赫数下,非对称翼型升力系数可提高15%;阻力系数减小16%;高马赫数下,通过控制使激波后移,对称翼型升力系数可提高17%。与传统机翼相比,这种自适应机翼负面效应小,不破坏机翼的结构,可以满足多种飞行状态下的气动需要。Aims at increasing the wing＇s lift and weakening the wing＇s shock wave, flow active control is studied by using the fluid mechanics. A new active control method based on piezoelectric elements is proposed, in which piezoelectric elements are buried on upper surface of winginduces periodic disturbance of boundary layer. The numerical simulation of the aerodynamic characteristics during the deformation process is done using the structural grid and the unsteady flow calculation method. The effect of piezoelectric elements on increasing the lift and weakening the shock of the aircraft wing is analyzed using computational fluid dynamics （CFD）. Most previous studies were confined in a two-dimensional airfoil numerical simulation. In this article, its computing method is extended to a three-dimensional wing model to verify the validity of the new control method. Research shows that through appropriate param- eter optimization, partial active deformation can improve the aerodynamic characteristics of airfoil. With the low roach number, the lift coefficient can be increased by 15% and the drag coefficient can be descended by 16% . The shock wave will move backward by control in the condition of high mach number and the lift coefficient of symmetrical airfoil can be improved by 17 % . The self-adaptive wing can meet aerodynamic needs in variety of conditions.

关 键 词：激波 结构网格 主动控制 三维机翼 

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]