超临界翼型的跨声速颤振特性研究  

On Comparing Flutter Characteristics of Three Supercritical Airfoils in Transonic Flow

作　　者：杨青[1] 闫锋[1] 杨永年[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2004年第6期782-785,共4页Journal of Northwestern Polytechnical University

基　　金：航空基础科学基金 (0 4 A5 30 0 6 );航天创新基金资助

摘　　要：采用 Navier- Stokes方程和二元弯 -扭颤振运动方程耦合 ,用时间推进方法计算结构响应的时间历程 ,从而得到超临界翼型的跨声速颤振特性。研究了结构参数完全相同的 3个超临界翼型( RAE2 82 2 ,DFVLR- R2和 NPU- 3)的跨声速颤振特性。为了对比 ,同时计算了 NACA0 0系列的 3个翼型 ( NACA0 0 1 2 ,NACA0 0 0 8,NACA0 0 0 4 )的跨声速颤振特性。研究结果表明 ,翼型形状对颤振特性有明显的影响 ,相对厚度较小的翼型颤振速度较高 ;厚度基本相同时 ,超临界翼型的颤振速度高于 NACA0 0系列翼型 ;跨声速范围内 ,由于气动力的非线性影响 。Flutter calculations using Navier-Stokes equations began circa 1990 and have come to be quite mature . Our aim is to apply this relatively mature method to investigate the effect of airfoil shape on flutter characteristics in transonic flow. We present a numerical investigation of flutter characteristics of three supercritical airfoils (RAE2822, DFVLR-R2, NPU-3) with two degrees of freedom--bending/torsion--in transonic flow. We couple an unsteady 2D compressible Navier-Stokes equation solver with two-degrees-of-freedom flutter motion equation in time domain. The three supercritical airfoils all have the same structural parameters: x α=0.25, r α=0.5, ω h/ω α=0.2, μ=1.25. The calculated results and graphs plotted from them show that: (1) in transonic flow, the airfoil shape influence on flutter velocity is obvious; the flutter velocity for smaller relative thickness is higher than that for larger relative thickness; (2) the flutter velocity of NPU-3 supercritical airfoil is higher than those for RAE2822 and DFVLR-R2; (3) the limit cycle oscillations for the three supercritical airfoils are significantly different.

关 键 词：超临界翼型 跨声速颤振 NAVIER-STOKES方程 极限环振荡 

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]