摘要
为满足带后缘小翼智能旋翼气动弹性分析的需求,建立一种基于代理方法的后缘小翼翼型气动力计算模型。模型从小翼偏转后的翼型实际形状出发,对带偏转小翼的翼型流场划分C型网格,基于二维黏性N-S方程求解流场计算翼型气动力。为方便气动弹性集成分析,节约求解非定常翼型气动力的时间成本,以RBF模型代理翼型CFD方法计算非定常翼型的环量气动力,以薄翼型理论计算气动力的非环量部分。以对称的NACA 0012翼型和非对称的NACA 23012翼型风洞试验数据和模型的计算结果对比,充分验证了模型计算常规翼型和带小翼翼型气动力的精度,同时证实了模型对不同翼型形状的适应性。
An agent based aerodynamic model for airfoil with trailing edge flap was built for aero-elastic analysis of smart rotors with trailing edge flaps. The flapped airfoil was directly modeled with a kind of C-shaped structural grid,and the flow filed was calculated with the viscous 2-dimensional Navier-Stokes function. For the convenience of aero-elastic analysis,the CFD method was surrogated by the radial based function,which was time saving during unsteady aerodynamic calculation. The noncirculation part of aerodynamic force was given in the form of thin airfoil theory. Both the symmetric airfoil NACA 0012 and the asymmetric airfoil NACA 23012 were calculated to validation the current aerodynamic model,comparisons between the wind tunnel test results and the calculated results confirm that the model can precisely calculating the aerodynamic force of conventional airfoil and flapped airfoil,and the model is fit for various airfoil shapes.
出处
《科学技术与工程》
北大核心
2016年第25期317-321,共5页
Science Technology and Engineering
关键词
直升机
旋翼
气动力
后缘小翼
代理模型
helicopter
rotor
aerodynamic
trailing edge flap
surrogate model
