马赫数变化对平板上方柱绕流特性的影响  

The influences of Mach number on the supersonic flow past a 3D-rectangular cylinder mounted on a plane

作　　者：薛大文[1] 陈志华[1] 孙晓晖[1] 韩珺礼[1] 

机构地区：[1]南京理工大学瞬态物理重点实验室,南京210094

出　　处：《空气动力学学报》2012年第6期754-760,共7页Acta Aerodynamica Sinica

基　　金：博士点基金(20103219110037)

摘　　要：基于大涡模拟方法,结合WENO格式以及自适应网格加密技术,对平板上三维方柱绕流分别在马赫数Ma=2.9和Ma=5.0条件下的绕流场进行了数值模拟。计算结果清晰显示了两种马赫数条件下,平板上分离区的旋涡结构以及尾涡形态的变化。详细讨论了来流马赫数变化对绕流流场结构的影响,数值模拟与相关实验结果相符,可为相关研究提供重要数据支持。Based on the large eddy simulation, combined with WENO scheme and the adaptive mesh re- finement technique, the supersonic flows of two Mach different numbers （Ma=2.9, 5.0） past a rectangular cylinder have been simulated. The numerical results revealed that both of the development of the vortex structures in the separation region and the wake vortices variations, and the influences of the Mach numbers on the vortex structures were discussed in detail. The calculated results are in good agreement with corre sponding experimental data which can provide important data for related researches.

关 键 词：超声速流动 方柱绕流 激波-边界层 数值模拟 

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]