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Identifying Opportunities for Reducing Nacelle Drag

[+] Author Affiliations
M. S. Zawislak, D. J. Cerantola, A. M. Birk

Queen’s University, Kingston, ON, Canada

Paper No. GT2017-63977, pp. V001T01A020; 10 pages
doi:10.1115/GT2017-63977
From:
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 1: Aircraft Engine; Fans and Blowers; Marine; Honors and Awards
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5077-0
  • Copyright © 2017 by ASME

abstract

The accurate prediction of drag caused by bluff bodies present in aerospace applications, particularly at high angles of attack, was a challenge. An experimental and numerical investigation of a nacelle intended for fuselage-mounted aircraft engines was completed at several angles of attack between 0 and 45 deg with a Reynolds number of 6 × 105. Steady-flow simulations were conducted on hybrid grids using ANSYS Fluent 15.0 with preference given to the realizable k-ε turbulence model. Both total drag and the pressure-to-viscous drag ratio increased with angle of attack as a consequence of greater flow separation on the suction surface. Near-field and far-field drag predictions had grid uncertainties below 2.5% and were within 10% of experiment, which were less than the uncertainties of the respective force balance and outlet traverse data at all angles of attack. Regions were defined on suction-side x-pressure force plots using the validated CFD data-set that showed where and how much drag could be reduced. At 20 deg angle of attack, there was potential to reduce up to 20% drag contained within the separated flow region.

Copyright © 2017 by ASME

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