高速冲压推进弹丸气动特性仿真分析  

Simulations analysis on aerodynamic characteristics of a high speed ramjet propelled projectile

作　　者：骆晓臣[1] 陈雄[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：《空气动力学学报》2013年第4期482-486,共5页Acta Aerodynamica Sinica

摘　　要：针对设计马赫数为4的冲压推进弹丸,采用数值仿真手段,分析了设计马赫数下进气道的工作特性。对被动段飞行的弹丸内、外部气动阻力进行了数值计算,分析了不同飞行马赫数条件下的弹丸气动阻力的变化。研究结果表明:设计马赫数下,冲压推进弹丸的进气道具备再起动能力,进气道亚临界状态最大总压恢复在0.25左右;在弹丸飞行的被动段,随着飞行马赫数从4降低到3,弹丸内部气动阻力系数几乎保持不变,在0.06左右;外部气动阻力系数由马赫数4下的0.16增加到马赫数3下的0.21,弹丸总的气动阻力系数由马赫数4下的0.23增加为马赫数3下的0.27。外部阻力中,摩擦阻力占约20%;内部阻力中,摩擦阻力占40%左右。The investigation on the aerodynamic characteristics of a high speed ramjet propelled projectile with the design Mach number of 4was performed by the method of numerical simulations.The internal and external drag acting on the projectile in passive flight phase was obtained through calculations.Variations of the drags were discussed at the range of Mach 4to Mach 3.The results show that the inlet studied in current paper can restart at the design Mach number;the maximum total pressure recovery of the inlet is about 0.25 at the sub-critical operational condition.When the passive flight Mach number decreases from 4to 3,the internal drag coefficient changes scarcely,it is nearly 0.06.While the external drag coefficient increases from 0.16at the Mach number of 4to 0.21at the Mach number of 3.The total drag coefficient ranges from 0.23 to 0.27while the Mach number decreases from 4to 3.The scale of friction drag is about 40%in internal drag and 20%in external drag.

关 键 词：冲压推进弹丸 混压式进气道 数值仿真 阻力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]