F321 2次元翼から発生する空力騒音の制御(F-32 騒音(2),一般講演)

概要

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In this paper we discuss, based on measured results, mechanisms of aerodynamic sound generated from a two-dimensional NACA0012 airfoil at various Reynolds number ranging from 2×10^5 to 4×10^5 and effects of reduction in surface treatment on sound by using pile fibers. On the stalled conditions, the coherence function between the surface pressure and radiated sound shows a peak value on all the positions of the airfoil chord at Strouhal number of about 0.6. The peak values of the coherence function gradually increase towards the trailing edge, and fluctuating surface pressures also show similar trend. This fluctuation seems to play a dominant role in sound generation from the stalled airfoil. We also tried to reduce the sound at this Strouhal number by putting pile fibers on various position of the airfoil chord. Some reduction in sound pressure level was obtained at this Strouhal number.
日本流体力学会の論文
2004-08-09