弹性机翼跨音速静气动弹性问题研究

在非结构网格基础上,采用有限体积法求解了Euler方程;在结构网格基础上,采用有限差分方法求解了N-S方程。同时采用结构影响系数法计及机翼结构系统的弹性影响,计算了弹性机翼的结构变形和气动力载荷。计算结果表明:后掠机翼结构系统的弹性使弹性机翼产生了正的挠度和负的剖面扭转角;负的扭转角使弹性机翼的有效迎角减小;有效迎角的减小又使得弹性机翼的有效气动力载荷减小。针对算例机翼结构系统的弹性使弹性机翼的升力相对刚性机翼的升力减小27.9%。

INVESTIGATIONS OF CHARACTERISTICS OF STATIC AEROELASTICITY FOR ELASTIC WING IN TRANSONIC FLOW

The characteristics of static aeroelasticity for elastic wing are calculated by two methods.One is solved based on 3-D Euler equations with cell-centered finite-volume algorithm,explicit Runge-Kutta time stepping scheme,on unstructured tetrahedral dynamic meshes.The other is solved based on 3-D N-S equations,with Non-oscillatory,containing No-free-parameters and Dissipative Lower Upper difference scheme,Baldwin-Lomax turbulence model,on structure C-H shape moving grids.The influence of wing elasticity is determined by structural influence coefficient method.The results show that the elastic deformation generate bending and torsion on the wing.The torsion reduces the effectual attack angle of the elastic sweep wing.In this paper,the lift of elastic wing decreases 27.9% in contrast to the designed rigid wing.