基于CFD/CSD方法的跨声速静气动弹性数值模拟应用研究  

Numerical applications on transonic static areoelasticity based on CFD/CSD method

作　　者：郭洪涛[1,2] 陈德华 张昌荣[2] 吕彬彬 王晓冰 

机构地区：[1]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 [2]中国空气动力研究与发展中心高速空气动力研究所,四川北川622763

出　　处：《空气动力学学报》2018年第1期12-16,共5页Acta Aerodynamica Sinica

摘　　要：针对大型飞机跨声速静气动弹性问题,基于CFD/CSD流固耦合方法开展了数值模拟应用研究。具体方法是:采用RANS方程与静气动弹性平衡方程作为计算控制方程,CFD采用多块对接结构化网格进行分区并行计算,并利用多重网格技术加速收敛;使用RBF结合TFI方法进行网格变形;通过TPS插值实现多场数据交换。基于上述方法开发了计算程序,并与典型风洞试验结果开展了对比研究,验证了方法和程序的有效性。最后通过数值模拟结果,分析了跨声速时静气动弹性对典型大型飞机机翼的几何变形、表面压力及气动性能的影响特性。A numerical simulation based on CFD/CSD method has been carried out to study the transonic static aeroelastic problems of large transporters.The specific methods are described as follows:the Reynolds-averaged Navier-Stokes equations(RANS)and the static aeroelastic balance equation are employed as the governing equations to conduct coupling iterative computation;a multi-block structured grid is generated for parallel CFD computation,and a multi-grid technique is adopted to accelerate convergence;the dynamic mesh generation is completed through the RBF combined with the TFI method;a three-dimensional thin plate spline interpolation technique is adopted to execute the data interchange between the flow field and structure.Based on the above methods and typical wind tunnel test data,a series of codes are developed and validated,and the results indicate the effectiveness of the methods.Finally,the deformation characters,the pressure distribution,and the aerodynamic performance of a typical large transporter's wing are analysed on the basis of the numerical results.

关 键 词：流固耦合 静气动弹性 数值模拟 大展弦比机翼 跨声速流动 

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]