基于各向异性非结构网格的超声速流动自适应计算  

Anisotropic unstructured mesh adaption for supersonic flow simulation

作　　者：邹建锋[1] 盛东[1] 邢菲[1] 张帅[1] 杨永健[1] 

机构地区：[1]浙江大学玉泉校区航空航天学院,浙江杭州310027

出　　处：《空气动力学学报》2013年第1期47-51,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金项目(10702064;11002125);航天支撑技术基金

摘　　要：基于各向异性非结构网格,实现了自适应求解技术,将其应用于超声速楔形体绕流及超声速横向喷流问题的计算研究,对各向异性网格自适应计算过程的收敛性和求解精度进行了对比分析,展示了各向异性网格自适应算法在降低问题求解规模。提高各向异性流场分辨率等方面的优势及存在的问题。超声速楔形体无粘绕流场的自适应计算,清晰地捕捉到了激波附近的流场信息,激波前后的马赫数、压力、密度。温度等物理量与理论分析解吻合很好。超声速横向喷流流场存在激波、分离涡、边界层等流场结构的相互干扰。计算研究表明,单纯基于Hes-sian度量张量的各向异性网格生成及自适应算法不能有效模拟边界层内的流动情况,是将来需要进一步开展的研究挑战。Anisotropic unstructured mesh adaption was developed and used to simulate supersonic flow problem, such as flow around supersonic wedge and injection into a supersonic stream. The ani-sotropic mesh adaption was gauged on the simulation of supersonic flow around wedge, which has exact analytic solu- tions, illustrating good agreement between the present results and the exact solutions for Mach number, pressure ratio, density ratio and temperature ratio. The capture of sharp discontinuities by using anisotropic grid is also illustrated through the simulation of supersonic wedge flow. The calculation of injection flow into a supersonic free stream demonstrates that the Hessian metric has difficulty in describing the mesh shape, mesh orientation and mesh scale within boundary layer area, though the convergence feature was found to be quite good, compared with the case of traditional isotropic mesh for the same problem.

关 键 词：各向异性非结构网格 度量张量 自适应求解 超声速楔形体绕流 超声速横向喷流 

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]