Three-Dimensional Effects on Plunging Airfoils at Low Reynolds Numbers

e-Archivo Repository

Show simple item record

dc.contributor.author Moriche Guerrero, Manuel
dc.contributor.author Gonzalo Grande, Alejandro
dc.contributor.author Flores Arias, Óscar
dc.contributor.author García-Villalba Navaridas, Manuel
dc.date.accessioned 2021-05-27T15:24:26Z
dc.date.available 2021-05-27T15:24:26Z
dc.date.issued 2020-10-01
dc.identifier.bibliographicCitation AIAA Journal, (2021), 59(1), pp. 64-74.
dc.identifier.issn 0001-1452
dc.identifier.uri http://hdl.handle.net/10016/32784
dc.description.abstract We present two-dimensional and three-dimensional (3-D) direct numerical simulations of large-amplitude plunging maneuvers at Reynolds numbers of Re=1000 and 5000, with velocity ratios of G=0.5, 1, and 2. For all cases, the evolution of the force coefficients is qualitatively similar. The lift coefficient presents a pronounced peak toward the end of the acceleration phase of the maneuver, a local minimum in the deceleration phase, and a second peak at the end of the maneuver. The amplitude of the main peak increases linearly with G, with limited effect of the Reynolds number and a negligible effect of the three-dimensionality of the flow. On the other hand, both the Reynolds number and three-dimensionality have a stronger effect on the amplitude of the maximum value of the lift coefficient at the end of the maneuver, as well as on the subsequent transient decay toward the static values. The comparison of the evolution of the flow structures near the airfoil shows that these differences in the force coefficients are due to subtle interactions between the various vortices generated during the maneuver, as well as to the development of a 3-D boundary layer on the suction side of the airfoil triggered by the instability of the trailing-edge vortices.
dc.description.sponsorship This work was supported by the State Research Agency of Spain (AEI) under grant DPI2016-76151-C2-2-R including funding from the European Regional Development Fund (ERDF). The computations were partially performed at the supercomputer Picasso from the Red Española de Supercomputación in activity FI-2018-2-0051. We thank A. Jones and G. Perrotta for providing their experimental data.
dc.format.extent 9
dc.language.iso eng
dc.publisher American Institute of Aeronautics and Astronautics
dc.rights © 2020 by M. Moriche, A. Gonzalo, O. Flores, and M. García-Villalba. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
dc.subject.other Freestream velocity
dc.subject.other NACA 0012
dc.subject.other Lift coefficient
dc.subject.other Direct numerical simulation
dc.subject.other Trailing edges
dc.subject.other Vortices
dc.subject.other Boundary layers
dc.subject.other Flow visualization
dc.subject.other Aspect ratio
dc.subject.other Convective boundary condition
dc.title Three-Dimensional Effects on Plunging Airfoils at Low Reynolds Numbers
dc.type article
dc.description.status Publicado
dc.subject.eciencia Aeronáutica
dc.identifier.doi http://doi.org/10.2514/1.J058569
dc.rights.accessRights openAccess
dc.relation.projectID Gobierno de España. DPI2016-76151-C2-2-R
dc.type.version acceptedVersion
dc.identifier.publicationfirstpage 65
dc.identifier.publicationissue 1
dc.identifier.publicationlastpage 74
dc.identifier.publicationtitle AIAA JOURNAL
dc.identifier.publicationvolume 59
dc.identifier.uxxi AR/0000027557
 Find Full text

Files in this item

*Click on file's image for preview. (Embargoed files's preview is not supported)


This item appears in the following Collection(s)

Show simple item record