摘要
采用基于径向基函数的无限插值方法进行了复杂外形的动网格生成,并针对其存在的可能导致壁面附近出现负体积与网格质量下降的问题,提出对不与物面直接相连的边的位移采用径向基函数插值,对与物面相连的边的位移进行线性插值获得位移量的方法解决该问题.采用无限插值方法建立了一种简单有效的物面相贯线处理方法.利用离散共轭方法计算目标函数梯度,对DLR-F6机翼-机身-短舱-挂架外形的机翼和短舱进行了几何外形参数化与气动外形优化设计.结果表明:考虑短舱安装方式的优化设计较不考虑短舱安装方式的优化设计可降低大约0.000 1的阻力系数.通过全机优化设计,将全机阻力系数降低了0.001 53.
A moving grid methodology based on transfinite interpolation（TFI）and radial basis function was adopted for complex configuration.For the problem that may lead to negative jacobian near configuration surface or decline of grid quality,a technology was proposed to remedy the flaw of TFI method：a radial basis function methodology was utilized to achieve the displacements of edges not directly linked to the configuration surface grid,and a linear interpolation was introduced to get the displacements of edges directly linked to the configuration surface grid.An efficient configuration surface grid movement method was introduced via TFI method in case of variation of junction lines.By use of descrete adjoint method to compute the gradient of objective function,wing and nacelle of DLR-F6wingbody-nacelle-pylon configuration was parameterized and optimized.Tests show that 0.000 1 of drag coefficient decline can be gained through optimization considering nacelle＇s position compared with optimization without considering nacelle＇s position.Totally,a decrease of 0.001 53aerodynamic drag coefficient can be obtained through optimization.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第9期2009-2015,共7页
Journal of Aerospace Power
基金
西北工业大学科技创新基金
关键词
复杂外形
气动优化设计
动网格
相贯线
短舱
离散共轭
complex configuration
aerodynamic design optimization
moving grid methodology
junction line
nacelle
discrete adjoint
