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(Referência obtida automaticamente do Web of Science, por meio da informação sobre o financiamento pela FAPESP e o número do processo correspondente, incluída na publicação pelos autores.)

Direct numerical simulations of the flow around wings with spanwise waviness

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Autor(es):
Serson, Douglas ; Meneghini, Julio R. ; Sherwin, Spencer J.
Número total de Autores: 3
Tipo de documento: Artigo Científico
Fonte: JOURNAL OF FLUID MECHANICS; v. 826, p. 714-731, SEP 2017.
Citações Web of Science: 10
Resumo

The use of spanwise waviness in wings has been proposed in the literature as a possible mechanism for obtaining improved aerodynamic characteristics, motivated by the tubercles that cover the leading edge of the pectoral flippers of the humpback whale. We investigate the effect of this type of waviness on the incompressible flow around infinite wings with a NACA0012 profile, using direct numerical simulations employing the spectral/hp method. Simulations were performed for Reynolds numbers of Re = 10 000 and Re = 50 000, considering different angles of attack in both the pre-stall and post-stall regimes. The results show that the waviness can either increase or decrease the lift coefficient, depending on the particular Re and flow regime. We observe that the flow around the wavy wing exhibits a tendency to remain attached behind the waviness peak, with separation restricted to the troughs, which is consistent with results from the literature. Then, we identify three important physical mechanisms in this flow. The first mechanism is the weakening of the suction peak on the sections corresponding to the waviness peaks. This characteristic had been observed in a previous investigation for a very low Reynolds number of Re = 1000, and we show that this is still important even at Re = 50 000. As a second mechanism, the waviness has a significant effect on the stability of the separated shear layers, with transition occurring earlier for the wavy wing. In the pre-stall regime, for Re = 10 000, the flow around the baseline wing is completely laminar, and the earlier transition leads to a large increase in the lift coefficient, while for Re = 50 000, the earlier transition leads to a shortening of the separation bubble which does not lead to an increased lift coefficient. The last mechanism corresponds to a sub-harmonic behaviour, with the flow being notably different between subsequent wavelengths. This allows the wing to maintain higher lift coefficients in some portions of the span. (AU)

Processo FAPESP: 14/50279-4 - Brasil Research Centre for Gas Innovation
Beneficiário:Julio Romano Meneghini
Linha de fomento: Auxílio à Pesquisa - Programa Centros de Pesquisa em Engenharia
Processo FAPESP: 12/23493-0 - Estudo numérico de asas com bordos de ataque e de fuga ondulados
Beneficiário:Douglas Serson
Linha de fomento: Bolsas no Brasil - Doutorado Direto