固体燃料冲压增程炮弹用混压式进气道数值模拟及实验研究  

Numerical Simulation and Experimental Investigation on Mixed-compression Inlet of Solid Fuel Ramjet Extended-range Projectile

作　　者：夏强[1] 武晓松[1] 孙波[1] 熊志平[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：《兵工学报》2010年第10期1372-1378,共7页Acta Armamentarii

摘　　要：利用三维雷诺平均Navier-Stokes方程,在不同攻角和来流马赫数条件下,对带侧向支柱的某固体燃料冲压弹用混压式进气道的内外复杂流场进行了数值模拟,并完成了风洞实验,得到了不同状态下进气道的纹影图片、沿程静压分布及进气道出口总压变化规律。结果表明:数值模拟所得流场结构与风洞实验纹影图一致;随着攻角的增大,流入进气道的空气流量减少,总压恢复系数降低,出口马赫数基本保持不变;在亚临界状态下,总压恢复系数受攻角的影响显著增大,其值甚至比临界状态时还要低;此外,在同一来流马赫数下,总压恢复系数随进气道出口反压的增大而增大。The complex flow field of a mixed-compression inlet of solid fuel ramjet extended-ranged projectile with struts was numerically simulated by using the 3D Reynolds-averaged Navier-Stokes equations in terms of different attack angles and inflow Mach numbers,and also the wind tunnel test was made.The schlieren photographs of inlet,the distribution of static pressure along the inlet and the influence of different operations on total pressure at the exit of inlet were obtained.The results indicate that the numerical flow structure and wind tunnel test schlieren photographs of inlet are identical.With the increase in angle of attack,the air flow enters into the inlet,the total pressure recovery coefficient decreases,and the Mach number of exit almost holds the line.At the subcritical state,the influence of attack angle on total pressure recovery coefficient increase significantly,and its value is lower than that in the critical state.Furthermore,under the same inflow Mach number,the total pressure recovery coefficient increases as the backpressure at the exit of inlet raises.

关 键 词：流体力学 混压式进气道 炮弹增程 风洞实验 数值模拟 

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]