使用RANS/LES混合方法对钝前缘三角翼进行数值模拟(英文)  

The application of numerical simulation of delta wing with blunt leading edge using RANS/LES hybrid method

作　　者：白俊强[1] 王波[1] 孙智伟[1] 

机构地区：[1]翼型、叶栅空气动力学国防科技重点实验室,西北工业大学,西安710072

出　　处：《空气动力学学报》2012年第3期373-379,共7页Acta Aerodynamica Sinica

摘　　要：阐述了建立在一方程湍流模型基础上的分离涡模型(DES)和延迟脱体涡模型(DDES),它们很好地模拟了壁面附近的小尺度流动。该方法在大攻角分离流区域,使用了亚格子应力的Smagorinsky大涡数值模拟,模拟亚音速旋涡流动。使用大攻角下的钝前缘65°大后掠三角翼模型,研究了CFD对涡的发展、破裂以及复杂涡的发展和演变的模拟能力。研究结果说明了方法对模拟分离流动是可行的。This article constructs detached eddy simulation（DES） and delayed detached eddy simulation（DDES） method based on one-equation turbulence model, which uses turbulence model to describe the small-scale movement near the wall. In the separated flow region, the method uses Smagorinsky large eddy simulation with sub-grid scale stress model function, simulating the characteristics of subsonic eddy flow at large angle of attack. The simulation capability of Computational Fluid Dynamics （CFD） on the development, breakdown of eddy and the development and evolution of complex eddy is validated using the blunt edge of the 65° delta wing at high angle of attack. The numerical simulation results indicate that the blunt edge of the 65° delta wing at high angle of attack. The numerical simulation results indicate that the method used in separated flow simulation is reliable.

关 键 词：分离涡模拟 延迟脱体涡模拟 分离流 数值模拟 湍流模型 

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]