基于非线性涡格法的快速静气动弹性数值模拟技术  

Fast Static Aeroelasticity Simulation Approach Based on Nonlinear Vortex Lattice Method

作　　者：孙岩[1,2] Andrea Da Ronch 王运涛[1] 孟德虹[1] 洪俊武[1] 许贤超 SUN Yan;Andrea Da Ronch;WANG Yun-tao;MENG De-hong;HONG Jun-wu;XU Xian-chao(Computational Aerodynamics Institution,China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Faculty of Engineering and Physical Sciences,the University of Southampton,Southampton SO171BJ,UK)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,四川绵阳621000 [2]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000 [3]南安普顿大学物理科学与工程学院,英国南安普顿SO171BJ

出　　处：《气体物理》2020年第6期26-38,共13页Physics of Gases

基　　金：国家重点研发计划课题(2016YFB0200703);国家数值风洞流固耦合模拟软件项目(NNW-FSI-2019)。

摘　　要：基于2.5D RANS数据和VLM耦合的方式,发展了一种考虑非线性流动效应的混合型涡格法HVLM.采用矩形直/后掠机翼两个外形的跨声速算例,通过与VLM、三维CFD计算数据的比较,对HVLM的气动力预测精度进行了分析与评估.对比结果表明,HVLM在大幅降低时间成本的前提下可以获得和三维CFD方法预测值十分接近的计算数据,对线化VLM方法的修正效果显著.然后,HVLM与悬臂梁有限元求解耦合,实现了一种面向三维机翼的快速静气动弹性数值模拟技术,并通过矩形直机翼算例进行了验证.耦合算例的时间分析数据表明,HVLM/Beam耦合的方式能够在10 s以内完成1次三维机翼静气动弹性分析,在气动/结构耦合分析、优化设计方面展示出了良好的应用前景.A hybrid vortex lattice method(HVLM)was developed based on the coupling between linear vortex lattice method and 2.5D RANS data.Two transonic flow cases of rectangular and swept wing were used to analyze and evaluate the prediction precision of the present HVLM,by comparing the simulation results with that obtained from the linear vortex lattice method and three-dimensional CFD.The comparison results between different methods show that the HVLM could correct the VLM data and obtain close results with the three-dimensional CFD method while reducing the time cost obviously.Then,a fast static aeroelasticity simulation approach was presented for the three-dimensional wing on the basis of the coupling between the HVLM and the finite element solution of cantilever beam.The rectangular wing was used to validate the coupling aeroelasticity simulation method.The time analysis data shows that a static aeroelasticity analysis on a three-dimensional wing could be finished in 10 s by the present coupling HVLM/Beam method.The simulation results demonstrate that the coupling scheme has a potential application in aero/structure coupling analysis and optimization design.

关 键 词：2.5D RANS 混合型涡格法 CFD 静气动弹性 悬臂梁 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]