混压式进气道与弹体一体化流场数值模拟  

Computation of the integrated flow field around missile and mixed compression intake

作　　者：李博[1] 梁德旺[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2002年第4期307-310,共4页Journal of Propulsion Technology

摘　　要：基于Favre平均的N S方程和B/L代数湍流模型 ,采用Jameson格式和矩阵人工粘性 ,对“X”布局的混压式超声速进气道与弹体的一体化流场进行了数值模拟。研究解决了数值计算中的附面层抽吸及混压式进气道的启动问题 ;得出了进气道内外流场的马赫数分布和速度分布 ;讨论了绕弹体非均匀来流条件下 ,进气道的位置、附面层抽吸及攻角对进气道性能的影响和进气道外型形状对弹体气动力的影响。结果表明 ,对混压式进气道必须进行附面层抽吸 ,进气道的位置对进气道的性能有很大的影响 。Based on the Favre averaged three dimensional compressible Navier Stokes equations and Baldwin Lomax algebraic turbulence model, the Jameson scheme and matrix artificial dissipation was used for simulation of the integrated flow field around a missile and mixed compression intakes in 'X' array Boundary layer suction and starting of mixed compression intake were first proposed in numerical simulation and the impact of boundary layer suction on the flow field was investigated The characteristics of the integrated flow field were discussed and the contour maps of Mach number and the velocity distribution were described The impact of the location of intakes, boundary layer suction and attack angle on the performance of intakes and the impact of the outer shape of intakes on the lift of the missile were also discussed The numerical results show that boundary layer suction is necessary to mixed compression intake It also shows the influence of the location and the outer shape of intakes The result can be referenced in the design of missile and intakes

关 键 词：混压式进气道 流场 弹体 数值模拟 一体化设计 计算流体动力学 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]