摘要
根据经典气动弹性响应模型和刚性动态失速模型,建立了二维弹性翼型动态失速下气弹响应的紧耦合模型;计算模型为典型动态失速风洞模型,应用最小二乘法拟合实验气动力得到了气动力模型;应用此气动力模型进行气动弹性响应紧耦合计算,结果表明,同样的条件下,弹性模型比刚性模型的动态失速现象会更明显,实际飞行攻角及升力的变化范围可能增大,弹性影响不可忽视。
A series of formulas are derived based on classical aeroelastic response model and rigid dynamic stall model, and a tight-couple aeroelastic response model for 2D dynamic stall is built. The simulation model is a typi- cal dynamic stall wind tunnel model, and an mathematical aerodynamic model is obtained by fitting experimental aerodynamic using Least Squares method. Then, tight-couple calculations of aeroelastic response using the fitted aerodynamic model are performed. Simulation results show that dynamic stall will be more serious for the elastic model. Compare with the rigid model, the range of angle of attack and the lift of the elastic model may be bigger.
出处
《科学技术与工程》
北大核心
2013年第32期9767-9770,共4页
Science Technology and Engineering
关键词
动态失速
气动弹性
弹性响应
紧耦合
dynamic stall aeroelasticity aeroelastic response tight couple
