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Effects of repetition rate and impulsiveness of simulated helicopter rotor noise on annoyance
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Author and Affiliation:
Powell, C. A.(NASA Langley Research Center, Hampton, VA, United States);
Mccurdy, D. A.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: Annoyance judgements were obtained for computer generated stimuli simulative of helicopter impulsive rotor noise to investigate effects of repetition rate and impulsiveness. Each of the 82 different stimuli was judged at 3 sound pressure levels by 48 subjects. Impulse repetition rates covered a range from 10 Hz to 115 Hz; crest factors covered a range from 3.2 dB to 19.3 dB. Increases in annoyance with increases in repetition rate were found which were not predicted by common loudness or annoyance metrics and which were independent of noise level. The ability to predict effects of impulsiveness varied between the noise metrics and was found to be dependent on noise level. The ability to predict the effects of impulsiveness was not generally improved by any of several proposed impulsiveness corrections. Instead, the effects of impulsiveness were found to be systematically related to the frequency content of the stimuli. A modified frequency weighting was developed which offers improved annoyance prediction.
Publication Date: Feb 01, 1982
Document ID:
19820011833
(Acquired Nov 13, 1995)
Accession Number: 82N19707
Subject Category: ENVIRONMENT POLLUTION
Report/Patent Number: NASA-TP-1969, L-14936
Document Type: Technical Report
Publisher Information: United States
Contract/Grant/Task Num: RTOP 505-35-13-01
Financial Sponsor: NASA; United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 59p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: ACOUSTIC SIMULATION; AIRCRAFT NOISE; HELICOPTERS; IMPULSES; NOISE MEASUREMENT; NOISE TOLERANCE; PRESSURE PULSES; PULSE RATE; REGRESSION ANALYSIS; ROTARY WINGS
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