Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel
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Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel report on the modified D.S.M.A. design

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Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English

Subjects:

  • Sound waves.,
  • Three dimensional models.,
  • Wind tunnel models.,
  • Scale models.,
  • Wind tunnels.,
  • Nozzle design.,
  • Wind tunnel nozzles.

Book details:

Edition Notes

StatementP.S. Barna.
SeriesNASA contractor report -- 198312., NASA contractor report -- NASA CR-198312.
ContributionsLangley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15504898M

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The Canadian Darrieus model tests were of and ft-diam rotors in a 30 × ft tunnel so the area ratio A r was about The Sandia model tests were of a 2-m-diam rotor in a × m tunnel, with A r again of the order of Thus both blockage correction factors had significance but were not large. 2 Wave equation, speed of sound, and acoustic energy. Order of magnitude estimates. Starting from the conservation laws and the constitutive equations given in section we will obtain after linearization a wave equation in the next section. Quiet rustling leaves 10 Normal Talking Hearing damage (long Approx 85 term exposure) Jackhammer/Disco 2 Approx Hearing damage (short 20 Approx term exposure) Rocket launch Approx Stun grenades Krakatoa eruption Approx at miles Theoretical limit for , undistorted sound Pa. The test campaign was conducted in the open-jet test section of the NASA Langley by foot Subsonic Tunnel on an 18%-scale, semi-span Gulfstream airframe model incorporating a trailing edge.