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Título : Droplet ratio deformation model in combination with droplet breakup onset modeling
Autor : García Magariño, A.
Sor, Suthyvann
Velázquez, Ángel
Palabras clave : Airfoil profiles;Leading edges;Aerospace technology;Drag coefficient;Weber numbers;Surface tension;Potential flow;Particle image velocimetry;Stagnation region;Data analysis
Fecha de publicación : 25-ago-2020
Editorial : Aerospace Research Central
DOI: 10.2514/1.C035942
Versión del Editor: https://arc.aiaa.org/doi/full/10.2514/1.C035942
Citación : Journal of Aircraft 58(2): 2021
Resumen : Droplet 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.
Descripción : Copyright © 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.
URI : http://hdl.handle.net/20.500.12666/895
ISSN : 1533-3868
Aparece en las colecciones: (Aeronáutica) Artículos

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