Record Details
| Subjective field study of response to impulsive helicopter noise | ||||
| NTRS Full-Text: | Click to View [PDF Size: 1.8 MB] | |||
| Author and Affiliation: |
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| Abstract: | Subjects, located outdoors and indoors, judged the noisiness and other subjective noise characteristics of flyovers of two helicopters and a propeller driven airplane as part of a study of the effects of impulsiveness on the subjective response to helicopter noise. In the first experiment, the impulsive characteristics of one helicopter was controlled by varying the main rotor speed while maintaining a constant airspeed in level flight. The second experiment which utilized only the helicopters, included descent and level flight operations. The more impulsive helicopter was consistently judged less noisy than the less impulsive helicopter at equal effective perceived noise levels (EPNL). The ability of EPNL to predict noisiness was not improved by the addition of either of two proposed impulse corrections. A subjective measure of impulsiveness, however, which was not significantly related to the proposed impulse corrections, was found to improve the predictive ability of EPNL. | |||
| Publication Date: | Apr 01, 1981 | |||
| Document ID: |
19810013343
(Acquired Nov 14, 1995)
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| Accession Number: | 81N21873 | |||
| Subject Category: | ACOUSTICS | |||
| Report/Patent Number: | NASA-TP-1833, L-14205 | |||
| 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: | 43p; In English | |||
| Distribution Limits: | Unclassified; Publicly available; Unlimited | |||
| Rights: | No Copyright | |||
| NASA Terms: | AIRCRAFT NOISE; EFFECTIVE PERCEIVED NOISE LEVELS; HELICOPTERS; NOISE PREDICTION (AIRCRAFT); PSYCHOACOUSTICS; DATA ACQUISITION; IMPULSES; REGRESSION ANALYSIS; ROTARY WINGS; ROTOR SPEED; TABLES (DATA) | |||
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