Aeroacoustic Investigation of a Propeller Operating at Low Reynolds Numbers
نویسندگان
چکیده
This paper presents an experimental investigation of a propeller operating at low Reynolds numbers and provides insights into the role aerodynamic flow features on both performances noise generation. A tip number regime is tested in anechoic wind tunnel advance ratio ranging from 0 to 0.6. Noise measured by means microphone array, while forces are with load torque cells. Oil-flow visualizations used show patterns blade surface, whereas phase-locked stereoscopic particle image velocimetry (PIV) measurements carried out analyze 60% radius. The pressure field around section has been computed PIV velocity data. Results reveal complex flowfield appearance laminar separation bubble suction side blade. moves toward leading edge reduces size as decreases. At equal 0.6, characterized without reattachment. causes vortex shedding responsible for high-frequency hump far-field spectra.
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ژورنال
عنوان ژورنال: AIAA Journal
سال: 2022
ISSN: ['0001-1452', '1533-385X', '1081-0102']
DOI: https://doi.org/10.2514/1.j060611