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dc.rights.licenseCopyright © 2020 by Instituto Nacional de Técnica Aeroespacial “Esteban Terradas”.es
dc.contributor.authorGarcía Magariño, A.es
dc.contributor.authorSor, Suthyvannes
dc.contributor.authorVelázquez, Ángeles
dc.date.accessioned2023-11-28T09:49:28Z-
dc.date.available2023-11-28T09:49:28Z-
dc.date.issued2020-08-25-
dc.identifier.citationJournal of Aircraft 58(2): 2021es
dc.identifier.issn1533-3868-
dc.identifier.otherhttps://arc.aiaa.org/doi/full/10.2514/1.C035942es
dc.identifier.urihttp://hdl.handle.net/20.500.12666/895-
dc.descriptionCopyright © 2020 by Instituto Nacional de Técnica Aeroespacial “Esteban Terradas”. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3868 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.es
dc.description.abstractDroplet deformation and breakup in the continuously accelerated flowfield generated by an incoming airfoil have been studied. The upper limit of droplet deformation and the minimum distance to the airfoil model at which the breakup onset takes place have been modeled. Three analytical equations have been developed based on the combination of two models: a droplet deformation and trajectory model for droplets in a continuously accelerated flowfield, and a breakup model for droplets in the vicinity of a leading edge of an airfoil model. The verification was made using experimental data obtained for water droplets whose diameters were in the range from 400 to 1800  μm impinging on airfoils of three different chord sizes moving at velocities from 50 to 90  m/s90  m/s. The rotating arm facility at National Institute of Aerospace Technology was used for this purpose. The analytical equations of the model were in good agreement with the experimental data. The upper limit of droplet deformation was verified by 95.40% of the tested experimental cases, and the minimum distance to the airfoil was verified in 99.65% of the cases.es
dc.description.sponsorshipThis investigation has been funded by the Ministry de Economy, Industry and Competitiveness of Spain (MINECO), as part of the project DFLOW DPI2016-75296-P. This investigation has also been funded by National Institute of Aerospace Technology, under the project “Termofluidodinámica.”es
dc.language.isoenges
dc.publisherAerospace Research Centrales
dc.relationinfo:eu-repo/grantAgreement/MINECO//DPI2016-75296-P/ES/DEFORMACIÓN Y ROTURA DE GOTAS CON Y SIN SOBRE-ENFRIAMIENTO EN FLUJOS DE INTERÉS AERONÁUTICO/es
dc.rightsAttribution-NonCommercial-NoDerivatives 4.0 Internationales
dc.rights.urihttps://creativecommons.org/licenses/by-nc-nd/4.0/es
dc.subjectAirfoil profileses
dc.subjectLeading edgeses
dc.subjectAerospace technologyes
dc.subjectDrag coefficientes
dc.subjectWeber numberses
dc.subjectSurface tensiones
dc.subjectPotential flowes
dc.subjectParticle image velocimetryes
dc.subjectStagnation regiones
dc.subjectData analysises
dc.titleDroplet ratio deformation model in combination with droplet breakup onset modelinges
dc.typeinfo:eu-repo/semantics/articlees
dc.identifier.doi10.2514/1.C035942-
dc.contributor.funderInstituto Nacional de Técnica Aeroespacial (INTA)es
dc.contributor.funderMinisterio de Economía y Competitividad (MINECO)es
dc.description.peerreviewedPeerreviewes
dc.type.hasVersioninfo:eu-repo/semantics/acceptedVersiones
dc.rights.accessRightsinfo:eu-repo/semantics/restrictedAccesses
dc.type.coarhttp://purl.org/coar/resource_type/c_6501es
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