基于响应面插值的非线性气动弹性计算

Based on the non-linear aeroelastic response surface interpolation calculation

摘要:

针对飞翼、大展弦比低雷诺数气动布局容易在小迎角的条件下出现气流分离,会带来明显的非线性气动力问题,同时气动弹性带来的影响亦不可忽略。针对此类布局提出了一种建立基于径向基函数插值的非线性压力系数分布模型的方法。利用径向基函数插值建立面元上压力系数对迎角导数的响应面,将压力系数积分并通过无限板样条(IPS)方法进行气动结构多次迭代插值实现非线性气弹分析。结果验证了该方法对于静气弹分析的有效性同时能准确地反映弹性带来的气动效率的降低和变形对升力及阻力的影响。

Abstract:

For flying wing, high aspect ratio low Reynolds number aerodynamic layout is easy in a small angle of attack occurs under conditions of flow separation, it will bring significant nonlinear aerodynamic problems, while the impact of aeroelastic problem also can not be ignored. For this type of layout presents a radial basis function interpolation to establish the non-linear pressure coefficient distribution model. Established by radial basis function interpolation surface element on the angle of attack on the pressure coefficient derivative response surface, the pressure coefficient points and through infinite plate spline (IPS) method of interpolation of multiple iterations to achieve aerodynamic structure nonlinear aeroelastic analysis. The results show that the method for static aeroelastic analysis of the effectiveness of flexibility while accurately reflect bring aerodynamic efficiency loss and distortion effects on lift and drag.