风洞模型静弹性变形对气动力影响研究

Static aeroelastic effects of wind tunnel model on aerodynamic forces

介绍了一种基于模型变形视频测量系统和计算空气动力学研究静弹性变形对气动力影响的方法。利用模型变形视频测量系统获取模型在气动载荷作用下的静弹性变形,驱动模型表面网格运动,得到模型变形后的表面CFD计算网格。CFD计算变形前后网格外形下的气动力,研究模型变形对模型气动特性的影响。对一大展弦比连接机翼的测量与计算结果进行了分析,分析结果表明:模型变形对升力系数影响最大发生在升力线性变化的最大迎角附近,模型变形对阻力系数影响最大发生在失速迎角附近,模型静弹性变形对气动力的最大影响量远远超出风洞测力实验的精度指标,因此开展风洞模型静弹性变形影响研究与修正是十分必要的。

Based on a model deformation video-measuring system, a method was presented to investigate static aeroelastic effects on aerodynamic forces based on a model deformation video measuring system and computational fluid dynamic. Static aeroelastic deformation of wing tunnel model under aerodynamic loads was measured by the system and was used to drive the original model surface mesh to move to get deformed surface mesh for CFD. Then CFD results of aerodynamic forces on original shape and deformed shape were acquired to investigate the static aeroelastic effects. Analysis on deformation measurements and computation- al results of a high aspect ratio joined wing shows that the maximum lift coefficient variation occurs near the maximum attack angle in linear region of lift force while the maximum drag coefficient variation occurs near the stall angle. The variation of aerodynamic forces caused by static aeroelastic deformation is far beyond the precision target set for wind tunnel aerodynamic forces tests. So, it is quite necessary to investigate and mod- ify static aeroelastic effects of wind tunnel model on aerodynamic forces.