大展弦比机翼模型设计对翼型流场气动特性的影响  

The effects of wind-tunnel model design on flowfield and aerodynamic behavior for large aspect-ratio wings

作　　者：武洁[1] 叶正寅[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,西安710072

出　　处：《实验流体力学》2009年第2期54-58,共5页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(10572120)

摘　　要：采用SST两方程湍流模型,通过求解非定常Navier-Stokes方程,模拟了大展弦比机翼风洞模型振动条件下的翼型流场,总结了翼型不同振动状况下的流场和气动力特点,分析了模型设计中的不同振动情况对风洞试验结果的影响。研究结果表明:在大展弦比机翼风洞模型的设计中,将翼型的重心设计在机翼的弹性轴之后,对风洞试验的精度较为有利。此结论对大展弦比机翼的风洞实验模型设计有指导意义。By solving unsteady Reynolds-averaged Navier-Stokes equations with SST turbulence model, the flowfields of the vibrating airfoils for wing models with large aspect-ratio in wind tunnel experiments were simulated. The flowfield and aerodynamic behavior of airfoils vibrating in different types were summarized, and the effects of designed models in different cases on the flowfield and aerodynamic behavior were investigated. It is shown that the vibrations of the airfoil can cause large-scale unsteady separated vortex shedding if the vibration amplitude reaches to a certain amount. When the centre of gravity of the airfoil locates downstream the elastic axis of the wing, the elastic vibration will have less effects on the flowfields and the aerodynamic behavior. This conclusion is valuable to the wing model design for wing tunnel experiments, especially for wind with large aspect-ratio.

关 键 词：分离流 非定常流 弹性振动 模型设计 

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]