This paper presents results from an experimental study of rotor blade-vortex interaction (BVI) aerodynamics and acoustics. The experiment utilized an externally generated vortex interacting with two-bladed rotor operating at zero thrust to minimize the influence of the rotor's own wake. The rotor blades were instrumented with a total of 60 absolute pressure transducers at three spanwise and ten chordwise stations on both the upper and lower surfaces. Acoustic data were obtained with fixed near-field microphones as well as a movable array of far-field microphones. The test was carried out in the acoustically treated test section of the NASA Ames 80- by 120-Foot Wind Tunnel. Several parameters which influence BVI, such as vortex-rotor separation distance, votrtex strength, and vortex sense (swirl direction), as well as rotor tip Mach number and advance ratio, were varied. Simultaneous measurements were obtained of blade surface pressure distributions, near-field acoustics, and far-field acoustics during the vortex-blade encounters.
A study of blade-vortex interaction aeroacoustics utilizing an independently generated vortex
Eine Untersuchung der gegenseitigen aeroakustischen Beeinflussung von Rotorblatt und Wirbelfluss unter Benutzung eines unabhängig erzeugten Wirbels
1995
19 Seiten, 18 Bilder, 11 Quellen
Conference paper
English
A Study of Blade-Vortex Interaction Aeroacoustics Utilizing an Independently Generated Vortex
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