摘要
采用非定常数值模拟的方法,研究了不同飞行马赫数、不同通道长径比条件下,超声速来流时封闭通道内的压强振荡幅度的变化。结果表明,压强振荡的极值和振幅与通道长径比无关;当飞行马赫数升高时,压强振荡的极值随来流总压近线性增加,绝对振幅增大,而相对于来流总压的振幅趋于不变;通道内振荡的平均压强与入口激波后总压相近,最大压强可能会超过来流总压。
The variation of pressure oscillation amplitude in closed supersonic duct was studied with different flight Mach number or duct length-to-diameter ratio by unsteady numerical simulations. The results show that the pressure oscillation extreme value and amplitude are independent of duct length-to-diameter ratio. When flight Mach number increases, the pressure oscillation extreme value nearly linear in- creases with total pressure of supersonic flow. The absolute amplitude increases, but the amplitude tends to be no change relative to total pressure. In duct, the average oscillation pressure is close to total pressure after shock. The maximum pressure possibly exceeds total pres-sure of supersonic flow.
出处
《弹箭与制导学报》
CSCD
北大核心
2013年第2期157-160,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
超声速流
非定常流
压强振荡
振幅
数值模拟
supersonic flow
unsteady flow
pressure oscillation
amplitude
numerica｜ simulation
