大展弦比后掠机翼静气弹效应对气动载荷的影响实验与分析

Test and study of static aeroelastic effects on wing's aerodynamic load

通过实验与理论分析结合的方法,针对静气弹效应对大展弦比后掠机翼气动载荷影响的问题进行了研究。加工了三副刚度各不相同的机翼,在一系列工况中进行风洞实验,对各个模型的气动载荷进行测量,通过对比可以得到机翼弹性对气动载荷的影响量。在理论分析中通过工程梁理论计算弹性机翼变形,通过升力面理论计算弹性变形引起的气动力增量,在二者之间迭代收敛后得到机翼弹性对气动载荷的影响量,并将其与实验结果进行对比。对比结果表明理论分析和实验吻合程度较好,表明了在机翼气动载荷计算中计入静气弹效应后,大展弦比后掠机翼的弯矩会有显著的降低,对于减轻结构重量有重要的意义。

This study presents the effects of static aeroelastic on aerodynamic loads for large ratio and sweepback wing according analytic and test methods.Three wing models of different stiffness are created and tested in the wind tunnel.The aerodynamic load is measured during the test.The static aeroelastic effects on wing load can be obtained by comparing the different wing load.For analytic approach,the wing’s deformation and aerodynamic increment are calculated based on engineering beam theory and lift surface theory,respectively.The consistency between analytic and test methods demonstrates that static aeroelastic effects on wing loads calculation can be highly useful for wing moments and structure weight reduction.