摘要
研究了附面层泄除对定几何混压式进气道起动马赫数、起动点性能和巡航点性能的影响,分析了放气槽的轴向位置、开口面积、出口面积和放气槽与当地气流夹角对进气道性能的影响,研究表明放气槽的轴向位置和出口面积对进气道性能影响较大,且在低马赫数下附面层泄除的影响更明显。最后设计了带放气槽的进气道,在典型状态下,总压恢复系数较原方案提高约7%。
In this paper the effect of boundary-layer bleed is studied on the mixed-compression inlet with fixed-geometry. The variety of the inlet＇ s starting Mach number and performance in starting and cruise state is analyzed when the bleed-slot changes the axial position, exit-area, entry-area and angle be- tween bleed-slot and flow-direction. The results show that the variable axial position and exit-area is more effective to change the performance of the inlet than the variable entry-area and angle between bleed-slot and flow-direction. In low-Mach flow the effect of boundary-layer bleed is more obvious. Finally redesign the inlet with bleed-slot, and it＇s total pressure recovery coefficient increase 7% in cruise state.
出处
《航空兵器》
2010年第2期28-31,41,共5页
Aero Weaponry
关键词
定几何混压式进气道
数值模拟
附面层泄除
起动
mixed-compression inlet with fixed-geometry
numerical simulation
boundary-layer bleed
start
