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结合飞/发一体化设计理念,以提升红外隐身性能为目的,引入横向掺混技术进行尾喷管构型设计。应用计算流体力学(CFD)数值仿真方法,分别分析了圆形喷管和矩形喷管流场温度分布,并提取矩形喷管中心面,研究喷管带小孔壁板偏折角对尾流冷却效果的影响。研究结果表明:相对于入口热流温度,矩形喷口降温率约为30%,尾气流喷出后偏向两侧流动,高温核心区体积快速衰减;圆形喷口降温率约为10%,尾气流喷出后沿轴向一直保持圆柱形,高温核心区体积衰减缓慢。矩形喷口主动冷却效果明显高于圆形喷口,更有利于实现飞/发一体化的热管理及红外隐身。同时,中面带小孔壁板偏折角的大小与主动冷却效果也存在密切关系。
With the integration of fly / hair design, with the aim of improving the performance of infrared stealth, transverse mixing technology is introduced to design the tail nozzle configuration. The CFD numerical simulation method was used to analyze the temperature distribution of the circular nozzle and the rectangular nozzle respectively. The center plane of the rectangular nozzle was extracted, and the effect of nozzle deflection angle on the wake cooling effect was studied Impact. The results show that the cooling rate of the rectangular nozzle is about 30% relative to the inlet heat flow temperature, the tail gas flow is deflected to both sides and the volume of the high temperature core area decays rapidly. The cooling rate of the circular nozzle is about 10% After the axial direction has remained cylindrical, high-temperature core area volume decay slowly. Rectangular spout active cooling effect is significantly higher than the circular spout, more conducive to achieve the fly / hair integrated thermal management and infrared stealth. At the same time, the size of the deflection angle of the wall plate with holes in the middle is also closely related to the active cooling effect.