Helicopter far-field acoustic levels as a function of reduced rotor speedsThis paper will present far-field measured noise levels relative to tests conducted with a model S-76A helicopter. The project was designed to provide supplemental experimental flight data which may be used to further study reduced helicopter rotor speeds (and thus, advancing blade-tip Mach number) effects on far-field acoustic levels. The aircraft was flown in straight and level flight while operating with both the rotor speed and flight speed as test variables. The rotor speed was varied over the range of 107 percent of the main-rotor speed (NR) to 90 percent NR and with the forward flight speed varied over the range of 155 to 35 knots indicated air speed. These conditions produced a wide range of advancing blade-tip Mach numbers to which the noise data are related.
Document ID
19920056604
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mueller, Arnold W. (NASA Langley Research Center Hampton, VA, United States)
Lemasurier, Philip (NASA Langley Research Center Hampton, VA, United States)
Smith, Charles D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Acoustics
Meeting Information
Meeting: NOISE-CON 90: National Conference on Noise Control Engineering