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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Design and performance study of a parametric diverterless supersonic inlet
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Design and performance study of a parametric diverterless supersonic inlet

机译：参数化无分流超音速进气道的设计与性能研究

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Diverterless supersonic inlet integration for a flight vehicle requires a three-dimensional compression surface (bump) design with an acceptable shock structure and boundary layer diversion; this results in a low drag induction system with acceptable propulsive efficiency. In this investigation, a computational fluid dynamics-based-generated bump is used to design an integrated diverterless supersonic inlet without any bleed mechanism on a forebody with a large wetted area. Numerical solution of the Navier-Stokes equations simulates the flow pattern of the configuration. The forebody design analysis includes simulating the effects of angle of attack and sideslip by dependent computational domains. Results demonstrate the ability of the bump surface to keep the shock structures in an operational mode even at high supersonic angles of attack. Analysis of shock structures and shock wave boundary layer interactions at supersonic maneuver conditions indicate that the aerodynamic efficiency of the diverterless supersonic inlet in conditions with a thick boundary layer and high angles of attack is sufficient to ensure operation throughout the supersonic flight envelope.
机译：飞行器的无分流超音速进气口集成需要具有可接受冲击结构和边界层分流的三维压缩表面（凸点）设计。这导致具有可接受的推进效率的低阻力诱导系统。在这项研究中，基于计算流体动力学的凸块用于设计集成的无分流超音速进气口，而前驱体上的湿润面积较大，没有任何排气机构。 Navier-Stokes方程的数值解决方案模拟了配置的流动模式。前体设计分析包括通过相关的计算域来模拟攻角和侧滑的影响。结果表明，即使在高超声速攻角下，凸块表面也能将冲击结构保持在工作模式。对超音速机动条件下的激波结构和激波边界层相互作用的分析表明，在具有厚边界层和高攻角的条件下，无分流超音速进气口的空气动力学效率足以确保整个超音速飞行包线的运行。

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