弹道学报2011，Vol.23Issue(4)：100-104,5.
超音速单轨火箭滑橇气动特性数值模拟
Numerical Simulation of Aerodynamic Characteristic of Supersonic Monorail Rocket Sled
张立乾 1邓宗才 2陈向东 1时瑾 3闫晶3
作者信息
- 1. 北京工业大学建工学院,北京100124
- 2. 总装备部工程设计研究总院,北京100028
- 3. 北京交通大学机电学院,北京100044
- 折叠
摘要
Abstract
Based on the three-dimensional viscous compressible Navier-Stokes equations,the aerodynamic characteristics of supersonic rocket sled flying near the ground were analyzed.The k-ω turbulence model were used in the numerical simulation.Triangular grid and quadrilateral grid were used to divide the computational domain,and the finite volume method was adopted to discretize the governing differential equations,and the above equations were solved by the implicit coupling algorithm.The effects of velocity and attack angle on the aerodynamic characteristics were numerically simulated.The results show that the surface pressure of the rocket head increases with the increase of Mach number;the head of the rocket flying at supersonic speed generates shock waves;the drag coefficient first gradually increases and then decreases with the increase of Mach number.Under the conditions of small attack angle,the drag and the lift change little,but the lateral force increases significantly with the increase of yaw angle.The results offer reference for the design of the supersonic rocket sled.关键词
火箭滑橇/气动特性/超音速/数值模拟Key words
rocket sled/aerodynamic characteristic/supersonic speed/numerical simulation分类
军事科技引用本文复制引用
张立乾,邓宗才,陈向东,时瑾,闫晶..超音速单轨火箭滑橇气动特性数值模拟[J].弹道学报,2011,23(4):100-104,5.
