NDLI: Rotor-vortex interaction noise

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Rotor-vortex interaction noise

Content Provider	NASA Technical Reports Server (NTRS)
Author	Schlinker, R. H. Amiet, R. K.
Copyright Year	1983
Description	A theoretical and experimental study was conducted to develop a validated first principles analysis for predicting noise generated by helicopter main-rotor shed vortices interacting with the tail rotor. The generalized prediction procedure requires a knowledge of the incident vortex velocity field, rotor geometry, and rotor operating conditions. The analysis includes compressibility effects, chordwise and spanwise noncompactness, and treats oblique intersections with the blade planform. Assessment of the theory involved conducting a model rotor experiment which isolated the blade-vortex interaction noise from other rotor noise mechanisms. An isolated tip vortex, generated by an upstream semispan airfoil, was convected into the model tail rotor. Acoustic spectra, pressure signatures, and directivity were measured. Since assessment of the acoustic prediction required a knowledge of the vortex properties, blade-vortes intersection angle, intersection station, vortex stength, and vortex core radius were documented. Ingestion of the vortex by the rotor was experimentally observed to generate harmonic noise and impulsive waveforms.
File Size	6097178
Page Count	131
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840002844
Archival Resource Key	ark:/13960/t6450hm34
Language	English
Publisher Date	1983-10-01
Access Restriction	Open
Subject Keyword	Acoustics Vortex Shedding Compressibility Effects Helicopters Blade-vortex Interaction Noise Prediction Aircraft Pressure Measurement Velocity Distribution Blade Slap Noise Void Ratio Rotary Wings Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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