计算矢量喷管流场的有限元法  

Finite Element Method to Calculate Vectored Nozzle Flowfields

作　　者：尤迎玖[1] 赵桂萍[1] 沈慧俐[1] 

机构地区：[1]西北工业大学

出　　处：《空气动力学学报》1998年第3期368-373,共6页Acta Aerodynamica Sinica

摘　　要：本文通过采用扫描有限元法及多步龙格－库塔时间推进格式求解非定常平均Ｎ－Ｓ方程来模拟二元矢量喷管的内部跨声速流场，成功地计算了二维有激波的跨声速喷管内部流场及俯仰角达３０°的三维矢量喷管内部流场，所得结果与国外文献及实验数据相符，证实了方法的精确性和实用性。文中采用的湍流模型为工程上广泛应用的Ｂ－Ｌ模型。In this paper,time dependent Runge Kutta,sweep finite element method is utilized to calculate the unsteady Navier Stokes equations in 2D/CD and 3D/CD (two and three dimensional convergent divergent) vectored nozzle viscous flowfields.The treatings of boundary conditions and turbulence model are also discussed here.The 2D and 3D transonic nozzle internal flowfields with shocks and pitch angle reaching 30° are successfully calculated.Satisfactory results are obtained which confinred by the foreign reference papers and data.It shows that the code developed in this paper is reliable and accurate.

关 键 词：喷管 N-S方程 扫描有限元法 矢量喷管 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]