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Aerodynamic performance of the adaptive nacelle inlet
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.ORCID iD: 0000-0002-2910-3770
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.ORCID iD: 0000-0002-9061-4174
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.ORCID iD: 0000-0003-0176-5358
2015 (English)In: 33rd AIAA Applied Aerodynamics Conference, 2015Conference paper, Published paper (Other academic)
Abstract [en]

The numerical aerodynamic investigations of an adaptive turbofan-engine inlet is per-formed. The adaptation is made on the front inner part of the inlet by changing positionsof two contour knots, which mimic the possible inlet structure morphing. The numericalcalculations are performed using Reynolds Averaged Navier-Stokes (RANS) simulations forthe climb condition. The evaluation of the aerodynamic performance is based on the inlettotal pressure recovery, DC60 parameter and standard deviation of the normal velocity atthe fan plane. The results exhibit common trend which is a shift of the evaluated parame-ters towards benecial level by increasing the radial position of the rst knot at the inletshape region which is close to the leading edge. Alteration of second knot, which is moredistant from leading edge, results in benecial performance for several inlet shapes. For allparameters, the same group of inlet shapes was isolated as a group of best performance.

Place, publisher, year, edition, pages
2015.
National Category
Fluid Mechanics and Acoustics
Identifiers
URN: urn:nbn:se:kth:diva-175824DOI: 10.2514/6.2015-3163OAI: oai:DiVA.org:kth-175824DiVA: diva2:862573
Conference
33rd AIAA Applied Aerodynamics Conference, Dallas, Texas, USA
Note

QC 20151023

Available from: 2015-10-22 Created: 2015-10-22 Last updated: 2015-10-23Bibliographically approved

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Majić, FraneEfraimsson, GunillaO'Reilly, Ciarán J.

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