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Influence of the Landing Gear Casing on A High Lift Aircraft

机译：起落架壳体对高升飞机的影响

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OWN (Over Wing Nacelle) configurations for integrated engines with an ultrahigh bypass ratio are designed as a part of a certain type of aircraft in order to get a lower noise. A landing gear casing needs to be designed to connect the nacelle with the wing. This paper has the topic of investigating on the influence of the landing gear casing on the high lift aircraft. To obtain the influence of the landing gear casing, a CAD model is designed firstly, after that mesh and simulation are done on the aircraft configuration with nacelle and landing gear casing. By comparing the results with the original configuration, the influence of the landing gear casing is obtained. Due to the installation of the landing gear casing, the lift coefficient increases by 9.96% from 0.1987 to 0.2185, while the drag coefficient increases by 5.04% from 0.0536 to 0.0563. There is no big influence on the pressure coefficient distribution of the aircraft configuration.
机译：具有超高旁通比的集成发动机的OWN（机翼机舱上方）配置被设计为某种飞机的一部分，以降低噪音。起落架壳体需要设计成将机舱与机翼连接起来。本文的主题是研究起落架壳体对高升力飞机的影响。为了获得起落架壳体的影响，首先设计了一个CAD模型，然后对具有机舱和起落架壳体的飞机构型进行了网格划分和模拟。通过将结果与原始配置进行比较，可以获得起落架壳体的影响。由于安装了起落架机壳，升力系数从0.1987增至0.2185，增幅为9.96％，阻力系数从0.0536增至0.0563，增幅为5.04％。对飞机配置的压力系数分布没有太大影响。

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