Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412

A NACA 4412 airfoil was tested, in a boundary layer wind tunnel, with the aim to study the effect of a Gurney mini-flap, as an active and passive flow control device submitted to a turbulent flow field. The main objective was the experimental determination of flow pattern characteristics downstream...

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Autores principales: Delnero, Juan Sebastián, Marañón Di Leo, Julio, Colman Lerner, Jorge León, García Saínz, Mariano Oscar, Muñoz, Federico, Hérouard, N., Camocardi, Mauricio Ezequiel
Formato: Articulo
Lenguaje:Inglés
Publicado: 2011
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Acceso en línea:http://sedici.unlp.edu.ar/handle/10915/84351
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id I19-R120-10915-84351
record_format dspace
institution Universidad Nacional de La Plata
institution_str I-19
repository_str R-120
collection SEDICI (UNLP)
language Inglés
topic Ingeniería Aeronáutica
Perfil alar
Gurney mini-flap
spellingShingle Ingeniería Aeronáutica
Perfil alar
Gurney mini-flap
Delnero, Juan Sebastián
Marañón Di Leo, Julio
Colman Lerner, Jorge León
García Saínz, Mariano Oscar
Muñoz, Federico
Hérouard, N.
Camocardi, Mauricio Ezequiel
Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
topic_facet Ingeniería Aeronáutica
Perfil alar
Gurney mini-flap
description A NACA 4412 airfoil was tested, in a boundary layer wind tunnel, with the aim to study the effect of a Gurney mini-flap, as an active and passive flow control device submitted to a turbulent flow field. The main objective was the experimental determination of flow pattern characteristics downstream the airfoil in the near wake. The untwisted wing model used for the experiments had 80cm wingspan and 50cm chord, with airfoil NACA 4412. The mini-flap was located on the lower surface at a distance, from the trailing edge, of 8%c (c airfoil chord). The Reynolds number, based upon the wing chord and the mean free stream velocity was 326,000 and 489,000. The turbulence intensity was 1.8%. The model was located into the wind tunnel between two panels, in order to assure a close approximation to two-dimensional flow over the model. As an active control device a rotating mini-flaps, geared by an electromechanical system (which rotate to a 30°) was constructed. The wake pattern and pressure values near the trailing edge were measured. The results obtained, for this mechanism, show us that the oscillating mini-flap change the wake flow pattern, alleviating the near wake turbulence and enhancing the vortex pair near the trailing edge at the mini-flap level and below that level, magnifying the effect described first by Liebeck [1]. That effect grows with the oscillating frequency. Additionally, the wake alleviation probably affects also the far wake. All of these facts suggest us to continue with the experiments, trying to measure the pressure distribution around the airfoil in all the cases, obtaining the lift and drag characteristics.
format Articulo
Articulo
author Delnero, Juan Sebastián
Marañón Di Leo, Julio
Colman Lerner, Jorge León
García Saínz, Mariano Oscar
Muñoz, Federico
Hérouard, N.
Camocardi, Mauricio Ezequiel
author_facet Delnero, Juan Sebastián
Marañón Di Leo, Julio
Colman Lerner, Jorge León
García Saínz, Mariano Oscar
Muñoz, Federico
Hérouard, N.
Camocardi, Mauricio Ezequiel
author_sort Delnero, Juan Sebastián
title Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
title_short Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
title_full Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
title_fullStr Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
title_full_unstemmed Aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil NACA 4412
title_sort aspects of the influence of an oscillating mini-flap upon the near wake of an airfoil naca 4412
publishDate 2011
url http://sedici.unlp.edu.ar/handle/10915/84351
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