摘要
在前期翼梢小翼外形参数优化工作的基础上,进一步研究和探讨了多级响应面法在机翼和翼梢小翼一体化设计中的应用。采用多级响应面法,数值模拟求解k-湍流模型的N-S方程,同时结合统计学分析方法,提高了计算效率和准确性。以最大升阻比为目标函数,约束升力系数和翼根弯矩系数。共选取了14个外形参数,进行了126次数值模拟试验。优化得到的最大升阻比为21.619。在优化得到的外形参数条件下,直接进行数值模拟试验得到的最大升阻比为21.640,两者相对误差为0.093%。与仅优化翼梢小翼的结果相比,机翼和翼梢小翼一体化设计得到的最大升阻比提高了4.64%,总阻力减少了6.25%,整机的气动性能得到进一步的提升。同时,翼根弯矩系数减少了4.55%,改善了对结构强度的设计限制。
Based on the former optimization of the winglet parameters,this paper accomplishs a further study and investigation of the application of the multi-level response surface method in the wing-and-winglet intergrated design.The calculating efficiency and accuracy are improved on the basis of the method and statistical analysis by solving the turbulence-model equations.The maximum lift-drag ratio is the objective function,and the lift coefficient and the wing-root bending moment are constraints.Fourteen shape parameters are selected,and one hundred and twenty-six numerical simulation experiments are done.The maximum lift-drag ratio of the optimization design is 21.619,and that of the direct numerical experiment is 21.640.The relative deviation is 0.093%.Compared with the winglet-only optimization results,the maximum lift-drag ratio of the wing-and-winglet intergrated design is increased by 4.64% with an accompanying decrease of 6.25% in total resistence.The aerodynamic performance of the aircraft is further promoted.Due to 4.55% decrease of the wing-root bending coefficient,the design restrictions of the structure strength are improved at the same time.
出处
《飞机设计》
2012年第5期36-39,共4页
Aircraft Design
关键词
翼梢小翼
气动优化
一体化设计
多级响应面法
winglet
aerodynamic opitimization
intergrated design
multi-level response surface method
