关键词: 混合压缩式进气道;一体化设计;计算流体动力学;附面层抽吸;数值仿真

Abstract: 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

Key words: Mixed compression intake;Integrated design;Computational fluid dynamics;Boundary layer suction;Numerical simulation