Abstract
Aerodynamic characteristics and noise fields of main rotors in hovering motion for UH-1H and UH-60 operated in Korean army were analyzed numerically. Unlike UH-1H blade, UH-60 blade has a 20˚ swept tip, which can decrease the wave drag at high speed range. A density-based compressible and incompressible solver of CFD++ was used for flow analysis. The Farassat formula 1A as a way of acoustic analogy was adopted for noise fields. Rotational speed of the blade set to maximum of design value, and any local shocks or delocalization of shocks from the blade were not observed at given rotational speed. FFT analysis was performed for timewise noise data, and overall sound pressure level (OASPL) was obtained based on the A-weighted scale. It turns out that the OASPL of UH-60 rotor at the designed tip speed shows 12 dB (18 dBA) lower than that of UH-1H one.
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