进气道布局对导弹气动性能影响的数值研究

Numerical Study of Inlet Configuration Effects on Aerodynamic Performance for Air-breathing Missiles

吸气式导弹布局形式多样,不同进气道布局形式对导弹的气动性能影响是不同的。为评价不同进气道布局形式对超音速空空导弹一体化内外流特性的影响,选取两种先进布局形式——腹部进气和双下侧45°进气导弹,基于FLUENT软件,采用CFD数值模拟技术,开展了进气道弹体内外流一体化的数值仿真计算。分析结果表明:外流特性上,双下侧进气导弹对流场空间的干扰范围较大,它的升阻力及俯仰力矩要大于腹部进气导弹,能提供较大的升力;而在内流特性上,腹部进气导弹的进气道性能优于双下侧进气导弹,更有利于发动机的正常工作。

Air-breathing missile has various configurations,while the aerodynamic performance of different inlet configuration missiles are different.In order to assess influence of different inlet configuration on missile aerodynamics and internal inlet flow field for supersonic air-to-air missile.Ventral inlet configuration and twin inlet configuration missiles were studied.CFD tool,FLUENT,was used to carry out numerical simulation of internal and external flow fields of inlet-body configuration missiles.Results show that twin inlet configuration missile has greater interference space for external flow field,which has better lift performance,its aerodynamics are greater than ventral inlet configuration missile,while ventral inlet is superior in inlet performance for internal inlet flow field,it＇s benefit for the motor.