超音速进气道三维流场数值仿真与性能分析  

Numerical Simulation and Performance Analysis on Three Dimensional Flow Field of Supersonic Inlet

作　　者：王筱蓉[1] 姜根柱[1] 周长省[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《计算机仿真》2010年第3期27-30,122,共5页Computer Simulation

摘　　要：减小冲压增程炮弹特别是进气道的阻力,可以提高炮弹的射程。建立了冲压增程炮弹超音速进气道的物理模型,采用N-S方程,并运用有限体积法对进气道进行了三维流场的数值仿真,得到了超音速进气道的流场结构图及性能参数,有利进行分析。重点研究了攻角对超音速进气道性能的影响。理论计算了进气道的总压恢复系数,并对进气道总压恢复系数的理论计算值与数值模拟值进行比较分析,基本一致。得到的结论为冲压增程炮弹提供了设计有效参考。To minimize resistances of ramjet assisted projectile and especially supersonic inlet can improve the fire range of it. Supersonic inlet model of ramjet assisted projectile was established, by solving Navier - Stokes equations and using finite volume method, numerical Ssimulation of three dimensional flow field for supersonic inlets were numerical simulated, and the contracture of supersonic inlet flow field and performance parameters were obtained and analyzed. Influence of attack angle to supersonic inlet performance was researched. By computing the total pressure recovery coefficient theoretically, the comparative analyses？ between theory computation results and numerical simulation results of inlet total pressure recovery coefficient were carried out, and the results were basically accordant. The conclusions provide theoretical references for reducing resistance and extending the fire range of ramjet assisted projectile.

关 键 词：冲压发动机 超音速进气道 有限体积法 数值仿真 性能分析 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]