摘要
以二维平板模拟红外窗口,应用数值方法研究了红外窗口气膜冷却的效果和规律.比较了射流切向喷射和大角度喷射下,气膜完全覆盖长度在不同的喷缝高度和总压比下的变化规律,并分析了射流在各种喷射角度下对窗口表面流场的影响.
Based on 2D plate to simulate infrared window, a numerical study is presented to determine the effects and rules of film cooling on infrared window. The effects of injection angle, slot height and total pressure ratio of injection flow and mainstream flow on the full film coverage length are studied. In addition, the effect of injection angle on the flow structure near the window is analyzed.
出处
《战术导弹技术》
2009年第1期24-29,共6页
Tactical Missile Technology
关键词
超声速
红外窗口
气动光学效应
气膜冷却
数值研究
supersonic
infrared window
aero-optical effect
film cooling
numerical study
