This work presents comparisons between experimental and numerical estimates of near-field rotor aeroacoustics in hover. The experiments took place at the Kazan National Research Technical University named after A. N. Tupolev (Kazan Aviation Institute). A set of rotor blades with NACA-0012 aerofoil sections was used to obtain the sound pressure distribution using a linear array of microphones. It is shown that CFD and experimental results are in good agreement suggesting that the obtained test data can be useful as a validation case for development of CFD tools.
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机译：这项工作提出了悬停的近场转子航空声学实验和数值估计之间的比较。实验是在喀山国立研究技术大学以A. N. Tupolev（喀山航空学院）命名的。一组带有NACA-0012翼型截面的转子叶片用于使用线性麦克风阵列获得声压分布。结果表明，CFD和实验结果吻合良好，表明所获得的测试数据可作为开发CFD工具的验证案例。
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