Abstract Bay cavity noise for full-scale nose landing gear: A comparison between experimental and numerical results
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Bay cavity noise for full-scale nose landing gear: A comparison between experimental and numerical results

机译：满刻度前起落架的海湾空腔噪声：实验结果与数值结果之间的比较

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AbstractThis paper presents results obtained from the wind tunnel testing of a highly detailed full-scale nose landing gear model of a regional aircraft. The full wheel bay, doors and a significant part of the fuselage are included in the model. The emphasis of this paper is on wheel bay cavity noise and its potential contribution to the far field at approach conditions and atM/mml:mo>0.2. A numerical analysis allows the pressure field in the wheel bay to be studied identifying the frequencies at which the Helmholtz resonance and the 3-D standing wave duct modes are excited by instabilities in the bay opening shear layer. Experimental results agree with those predicted, with the empty wheel bay radiating tones of up to 12 dB at the Helmholtz resonance, at two duct modes as well as at interaction tones between them. The Rossiter equation is successfully used to explain fluid-resonant lock-on between the shear layer instability modes and the excited resonant modes as a function of tunnel velocity. However, when the full landing gear and doors are installed into the empty bay model, these bay tones no longer radiate to the far field. It is concluded that this is due to disruption of the shear layer by this particular nose landing gear configuration whose leg is centrally located and whose drag and side-stays occupy a large area of the wheel bay opening.
机译： 摘要 本文介绍了从风洞测试中获得的结果，该测试是对一架支线飞机的高度详细的全尺寸前起落架模型进行的测试。该型号包括全轮舱，门和机身的重要部分。本文的重点是轮舱腔噪声及其在进近条件和 M / mml：mo> 0.2 。数值分析可以研究轮舱中的压力场，从而确定由舱口开口剪切层中的不稳定性激发亥姆霍兹共振和3-D驻波导管模式的频率。实验结果与预测的结果一致，空轮舱在亥姆霍兹共振，两种风道模式以及它们之间的相互作用声调下辐射音调高达12 dB。 Rossiter方程已成功地用于解释剪切层失稳模式和受激共振模式之间的流体共振锁定，该锁定是隧道速度的函数。但是，当将完整的起落架和门安装到空舱模型中时，这些舱室的音调将不再辐射到远场。结论是，这是由于这种特殊的前起落架结构破坏了剪切层，前起落架结构的腿位于中央，阻力和侧撑占据了轮舱开口的大部分区域。

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