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首页> 外文期刊>Chinese journal of aeronautics >Design and Wind Tunnel Study of a Top-mounted Diverterless Inlet
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Design and Wind Tunnel Study of a Top-mounted Diverterless Inlet

机译：顶置无分流进气口的设计和风洞研究

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摘要

Combined with a UAV of the shape like Global Hawk, a new inlet is advanced to obtain high performance in both Radar Cross Section(RCS) and aerodynamic drag. Efforts are made to achieve this goal such as adopting a top-mounted inlet configuration, utilizing the diverterless technique and putting forward a new shape of entrance. A design method is brought forward and verified by wind tunnel tests. Results indicate: (1) Despite the negative effect of the front fuselage and the absence of the conventional boundary diverter, the performance of the top-mounted diverterless inlet advanced here (Ma : 0 .50-0.70, alpha: - 4 deg-6 deg, sigma > 0 .975) is equivalent to that of conventional S shaped inlet with diverter; (2) The integration of the inlet with the fuselage is realized by the utilization of a special inlet section and the diverterless technique, which disposes the whole inlet in the shield of the head of UAV, improving the drag characteristics and the stealthy performance of the aircraft; (3) The bump which is equal to the local boundary layer thickness in height can divert the boundary layer effectively. As a result, no obvious low total pressure zone is found at the outlet of the inlet; (4) According to the experimental results, negative angle of attack is favorable to the total pressure recovery and positive angle of attack is favorable to the total pressure distortion, while yaw brings bad effects on both; (5) The design of cowl lip is of great importance to the inlet performance at yaw, therefore, further improvement of the inlet performance will rely on the lip shapes of the cowl chosen.
机译：结合形状像Global Hawk的无人机，先进的新进气口在雷达横截面（RCS）和气动阻力方面均获得了高性能。努力实现此目标，例如采用顶部安装的入口配置，利用无分流技术并提出新的入口形状。提出了一种设计方法，并通过风洞试验进行了验证。结果表明：（1）尽管前机身有不利影响并且没有常规的边界分流器，但顶部安装的无分流器进气口的性能在此有所提高（Ma：0 .50-0.70，alpha：-4 deg-6 deg，sigma> 0 .975）等效于带分流器的传统S形入口； （2）进气口与机身的整合是通过利用特殊的进气口部分和无分流技术实现的，该技术将整个进气口布置在无人机头部的防护罩中，从而改善了阻力特性和隐身性能。飞机; （3）等于高度的局部边界层厚度的凸块可以有效地转移边界层。结果，在入口的出口处没有发现明显的低总压力区。 （4）根据实验结果，负攻角有利于总压力恢复，正攻角有利于总压力畸变，而偏航对两者均造成不良影响。 （5）前围唇的设计对于偏航时的进气性能至关重要，因此，进气性能的进一步提高将取决于所选前围的唇形。

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