空气动力学学报2019，Vol.37Issue(3)：382-392,11.
雷诺数对机翼尾缘噪声的影响
Reynolds number effects on tonal noise generation from an airfoil
摘要
Abstract
The tonal noise generation from a NACA0015 airfoil at a low (Re c＝1×104 )and a moderate (Re c＝5× 104 )Reynolds number is studied by performing two-dimensional direct numerical simulations.The effects of Reynolds number result in distinguishing features on the acoustic fields and thus the spectra.For the moderate Reynolds number cases,the vortex shedding on the suction and pressure side of the airfoil contributes separately to the generation of the acoustic waves,corresponding to an individual hump with different discrete frequencies in the acoustic spectra.A linear stability analysis is used to clarify the relation between the formation of vortices with the growth of unstable Tollmien-Schlichting (T-S)waves.Results suggest that the single tone observed in the low Reynolds number cases is probably associated with the inherent hydrodynamic instability of the boundary layer, whereas the multiple tones in the moderate Reynolds number cases are considered to be associated with a feedback loop mechanism between the formation of vortices and the excitation of acoustic disturbances.Feedback loops actually exist on both sides of the airfoil rather than just on the pressure side or on the suction side of the airfoil.关键词
机翼尾缘噪声/雷诺数影响/闭环反馈机制/线性不稳定性分析/NACA0015 翼型Key words
trailing edge noise/ Reynolds number effect/ feedback loop mechanism/ linear stability analysis/NACA0015 airfoil分类
航空航天引用本文复制引用
XU Siwei,LI Weipeng..雷诺数对机翼尾缘噪声的影响[J].空气动力学学报,2019,37(3):382-392,11.基金项目
国家自然科学基金(11772194) （11772194）
上海市地面交通工具空气动力与热环境模拟重点实验室开放课题基金(VATLAB-2018-02) （VATLAB-2018-02）
