Model helicopter rotor impulsive noise

An investigation of helicopter rotor blade slap was performed on a 1·27 m diameter model rotor. The rotor blades were a NACA 0012 section with a −8° linear twist. The experiments were conducted in the M.I.T. Anechoic Wind Tunnel. The effects of number of blades, blade pitch, advance ratio, and shaft...

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Veröffentlicht in:	Journal of sound and vibration 1981-10, Vol.78 (3), p.425-437
Hauptverfasser:	Hubbard, J.E., Harris, W.L.
Format:	Artikel
Sprache:	eng
Online-Zugang:	Volltext
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