The cost of noise reduction in commercial tilt rotor aircraft
Name
FTL_R_1974_05.pdf
Size
9.94 MB
Format
Adobe PDF
Checksum (MD5)
afcc4f1428bf4f9b8730a354b9aa1811
Author(s)
Faulkner, Henry B.
Date Issued
1974
Publisher
Cambridge, Mass. : Flight Transportation Laboratory, Massachusetts Institute of Technology, [1974]
Series/Report no.
NASA contractor report ; NASA CR-137552
FTL report (Massachusetts Institute of Technology. Flight Transportation Laboratory) ; R74-5
Abstract
The relationship between direct operating cost and departure noise annoyance was developed for commercial tilt rotor aircraft. This was accomplished by generating a series of tilt rotor aircraft designs to meet various noise goals at minimum DOC. These vehicles were spaced across the spectrum of possible noise levels from completely unconstrained to the quietest vehicle that could be designed within the study ground rules. A group of optimization parameters were varied to find the minimum DOC while other inputs were held constant and some external constraints were met. This basic variation was then extended to different aircraft sizes and technology time frames. It was concluded that reducing noise annoyance by designing for lower rotor tip speeds is a very promising avenue for future research and development. It appears that the cost of halving the annoyance compared to an unconstrained design is insignificant and the cost of halving the annoyance again is small.
Description
August 1974
Includes bibliographical references (p. 48-50)
Subjects
Vertically rising aircraft
Helicopters
Noise
Persistent DSpace Link
