Publication:
Characterization of Aerodynamic Forces on Wings in Plunge Maneuvers

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dc.affiliation.dptoUC3M. Departamento de Ingeniería Aeroespaciales
dc.affiliation.grupoinvUC3M. Grupo de Investigación: Ingeniería Aeroespaciales
dc.contributor.authorMoriche Guerrero, Manuel
dc.contributor.authorSedky, Girguis
dc.contributor.authorJones, Anya R
dc.contributor.authorFlores Arias, Óscar
dc.contributor.authorGarcía-Villalba Navaridas, Manuel
dc.contributor.funderMinisterio de Ciencia e Innovación (España)es
dc.date.accessioned2021-05-27T14:23:14Z
dc.date.available2021-05-27T14:23:14Z
dc.date.issued2021-02-01
dc.description.abstractWe present experiments and simulations of plunging maneuvers of large amplitude, for velocity ratios of G=1 and 2, defined as the ratio between the peak plunge velocity and the freestream velocity. We explore the effect of the airfoil shape by considering a NACA 0012 wing and a flat plate. The experiments are performed with wings with aspect ratios of 4 and 4.86, whereas the simulations are performed using a model of an infinite-aspect-ratio wing. We report the time evolution of the force coefficients and flow visualizations. A good qualitative agreement is found between experiments and simulations, with small discrepancies in the maximum and minimum lift coefficients observed during the maneuvers and somewhat larger discrepancies during the postmaneuver phase. It is found that the airfoil shape has a small effect on the lift coefficient but a somewhat larger effect on the drag coefficient. We also perform a force decomposition analysis to relate vortical structures to the force on the wings, providing a quantitative measurement of the effect of the leading-edge vortex and trailing-edge vortex on the peak aerodynamic forces.en
dc.description.sponsorshipThis work was partially supported by the State Research Agency of Spain (AEI) under grant DPI2016-76151-C2-2-R, including funding from the European Regional Development Fund and the U.S. Air Force Office of Scientific Research under grant FA9550-16-1-0508. The computations were partially performed at the supercomputer Picasso from the Red Española de Supercomputación in activity FI-2019-1-0030.en
dc.description.statusPublicadoes
dc.format.extent11
dc.identifier.bibliographicCitationAIAA Journal, (2021), 59(2), pp. 736-747.en
dc.identifier.doihttps://doi.org/10.2514/1.J059689
dc.identifier.issn0001-1452
dc.identifier.publicationfirstpage736
dc.identifier.publicationissue2
dc.identifier.publicationlastpage747
dc.identifier.publicationtitleAIAA JOURNALen
dc.identifier.publicationvolume59
dc.identifier.urihttps://hdl.handle.net/10016/32782
dc.identifier.uxxiAR/0000027556
dc.language.isoengen
dc.publisherAmerican Institute of Aeronautics and Astronauticsen
dc.relation.projectIDGobierno de España. DPI2016-76151-C2-2-Res
dc.rights©2020 by M. Moriche, G. Sedky, A. R. Jones, O. Flores, and M. García-Villalba. All rights reserved.en
dc.rights.accessRightsopen accessen
dc.subject.ecienciaAeronáuticaes
dc.subject.otherFreestream velocityen
dc.subject.otherSymmetric airfoilen
dc.subject.otherTrailing edgesen
dc.subject.otherFlow visualizationen
dc.subject.otherAspect ratioen
dc.subject.otherVortex breakdownen
dc.subject.otherLift coefficienten
dc.subject.otherDirect numerical simulationen
dc.subject.otherIncompressible flowen
dc.subject.otherWing configurationsen
dc.titleCharacterization of Aerodynamic Forces on Wings in Plunge Maneuversen
dc.typeresearch article*
dc.type.hasVersionAM*
dspace.entity.typePublication
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