HyperFLOW亚跨声速流动验证（英文）  

Validation of HyperFLOW in Subsonic and Transonic Flow

作　　者：赫新[1,2] 赵钟[1] 马戎[1] 王年华[1] 张来平[1,2] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000 [2]空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2016年第2期267-275,共9页Acta Aerodynamica Sinica

基　　金：Supported by National Science Foundation of China(No.11272339)

摘　　要：主要介绍了结构/非结构混合CFD软件HyperFLOW的设计开发与验证。HyperFLOW软件在结构网格上采用结构算法,在非结构网格上采用非结构算法,以充分利用两种网格及解算器的优点。首先介绍了软件的体系结构和基本算法,然后采用NASA Trap-Wing高升力外形和DLR-F6翼身组合体,对软件的结构解算器和非结构解算器进行了验证。结果表明,该软件的结构解算器和非结构解算器均有较好的网格收敛性,计算结果与其他参考结果和试验数据均符合较好,具有可接受的可信度。HyperFLOW,a structured/unstructured hybrid CFD software,is introduced in this paper.For HyperFLOW,the structured solver runs on structured grids,while the unstructured solver runs on unstructured grids,in order to fully take advantages of both grids and solvers.The architecture of HyperFLOW is briefly introduced firstly.Then,some typical cases are tested to validate both the structured and unstructured solver,including the Trap-Wing configuration from HiLiftPW-I and the DLR-F6 wing-body configuration from DPW-II.The performance of grid convergence is studied for both solvers.The numerical results demonstrate that HyperFLOW has good grid convergence property on both structured and unstructured grids.The computational results match well with the reference and experimental data,indicating acceptable credibility.

关 键 词：HyperFLOW CFD软件 NASA Trap-Wing高升力外形 DLR-F6翼身组合体 

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]