摘要
针对具有自适应后缘的跨声速翼型,基于代理模型和遗传算法相结合的优化方法,开展考虑自适应后缘结构约束的翼型气动优化设计研究。结果表明,低升力系数下翼面流场没有明显的能量损失,不同设计升力系数得到的自适应后缘翼型阻力相差不大;高升力系数下翼面附近存在激波,翼型阻力主要由激波强度决定。对于以低升力系数为设计点的基本翼型,通过后缘自适应变弯来调整载荷分布,可以降低翼面激波强度,减小翼型阻力;对于以高升力系数为设计点的基本翼型,可以直接通过气动优化来消除翼面激波,使得翼型阻力达到最小。因此对于带有自适应后缘的翼型,为了实现宽升力系数范围内的阻力最小,应首先以高升力系数为设计点完成基本翼型的气动优化设计,然后以低升力系数为设计点完成自适应后缘外形的气动优化设计。
Aiming at the aerodynamic design problem of transonic airfoil with adaptive trailing edge,based on the integrated method of surrogate model and genetic algorithm,transonic airfoil aerodynamic optimization design with the constraint of structure on the adaptive trailing edge was investigated.The results show that:there is almost no obvious energy loss in the flow field under the condition of low lift,and the drag of airfoils obtained by different design lift nearly the same through trailing edge deformation.On the contrary,the energy loss in the flow field is mainly caused by shock wave at high lift,as a result,the airfoil drag mostly depends on the intension of the shock wave near the wall.For the airfoil designed at low lift,adaptive trailing edge can be used to reduce drag by adjusting the aerodynamic load distribution,in contrast,for the airfoil designed at high lift,the drag can be reduced to the least by being redesigned into a shock free airfoil.As a consequence,to let the drag to the minimum at wide lift range for the airfoil with adaptive trailing edge,the base shape should be optimized at high lift,and the shape of adaptive trailing edge should be designed at low lift.
作者
李春鹏
张铁军
钱战森
Li Chunpeng;Zhang Tiejun;Qian Zhansen(Aero Science Key Lab of High Reynolds Aerodynamic Force at High Speed,AVIC Aerodynamics Research Institute,Shenyang 110134,China)
出处
《航空科学技术》
2019年第11期41-47,共7页
Aeronautical Science & Technology
关键词
翼型
自适应后缘
气动优化
结构约束
代理模型
airfoil
adaptive trailing edge
aerodynamic optimization
structural constraint
surrogate model
