带单锥和双锥混压式进气道的冲压增程弹丸气动特性仿真分析  

Simulations analysis on aerodynamic characteristics of ramjet projectiles with single-cone and double-cone mixed compression inlets

作　　者：骆晓臣[1] 周长省[1] 鞠玉涛[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1期110-114,共5页Acta Aerodynamica Sinica

摘　　要：针对带单锥和双锥混压式进气道的两种冲压增程弹丸,对比分析了单、双锥混压式进气道的特点。采用仿真手段,对弹丸外部气动阻力和进气道工作特性进行了数值计算,分析了不同飞行马赫数条件下的弹丸外部气动阻力的变化、进气道临界状态下的总压恢复、捕获流量特性,并分析讨论了进气道的起动特性。研究结果表明:在飞行马赫数2.65到1.75之间,两种冲压增程弹丸的外部气动阻力几乎相同;在飞行马赫数1.75下,两种冲压增程弹丸进气道均能够起动;在低于设计马赫数时,进气道临界状态下,单锥进气道的捕获流量和总压恢复特性均优于双锥进气道,冲压增程弹丸采用单锥进气道将更为合适。The characteristics of mixed-compression inlets used for ramjet projectiles with single-cone and double-cone external compression were analyzed. The external aerodynamic drag act on the projectiles and characteristics of the two inlets were calculated by method of numerical simulations. The variation of external aerodynamic drag was presented when the flight Mach number ranged from 2.65 to 1.75. The total pressure recovery and mass flow ratio at critical operational conditions were discussed comparatively between the two inlets with the decrease of the flight Mach number. Results of numerical simulations show that the drag acts on the projectile with different inlet was comparable; both inlets can start at the Mach number of 1.75; when the flight Mach number was below the design Mach number, both the total pressure recovery and mass flow ratio of the mixed compression inlet with single-cone external compression were superior to those of the mixed compression inlet with double-cone external compression. Then, mixed compression inlet with single- cone external compression is preferable for ramjet projectile.

关 键 词：冲压增程弹丸 进气道 数值模拟 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]