Bashir, M., Zonzini, N., Martel, S. L., Botez, R. M., Ceruti, A. et Wong, T..
2024.
« Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method ».
Aeronautical Journal, vol. 128, nº 1321.
pp. 441-468.
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Résumé
This paper investigates the effect of the optimised morphing leading edge (MLE) and the morphing trailing edge (MTE) on dynamic stall vortices (DSV) for a pitching aerofoil through numerical simulations. In the first stage of the methodology, the optimisation of the UAS-S45 aerofoil was performed using a morphing optimisation framework. The mathematical model used Bezier-Parsec parametrisation, and the particle swarm optimisation algorithm was coupled with a pattern search with the aim of designing an aerodynamically efficient UAS-45 aerofoil. The γ − Reθ transition turbulence model was firstly applied to predict the laminar to turbulent flow transition. The morphing aerofoil increased the overall aerodynamic performances while delaying boundary layer separation. Secondly, the unsteady analysis of the UAS-S45 aerofoil and its morphing configurations was carried out and the unsteady flow field and aerodynamic forces were analysed at the Reynolds number of 2.4 × 106 and five different reduced fre- quencies of k = 0.05, 0.08, 1.2, 1.6 and 2.0. The lift (CL), drag (C D) and moment (C M ) coefficients variations with the angle-of-attack of the reference and morphing aerofoils were compared. It was found that a higher reduced fre- quencies of 1.2 to 2 stabilised the leading-edge vortex that provided its lift variation in the dynamic stall phase. The maximum lift (C L,max ) and drag (C D,max ) coefficients and the stall angles of attack are evaluated for all studied reduced frequencies. The numerical results have shown that the new radius of curvature of the MLE aerofoil can minimise the streamwise adverse pressure gradient and prevent significant flow separation and suppress the formation of the DSV. Furthermore, it was shown that the morphing aerofoil delayed the stall angle-of-attack by 14.26% with respect to the reference aerofoil, and that the C L,max of the aerofoil increased from 2.49 to 3.04. However, while the MTE aerofoil was found to increase the overall lift coefficient and the CL,max, it did not control the dynamic stall. Vorticity behaviour during DSV generation and detachment has shown that the MTE can change the vortices’ evolution and increase vorticity flux from the leading-edge shear layer, thus increasing DSV circulation. The conclusion that can be drawn from this study is that the fixed drooped morphing leading edge aerofoils have the potential to control the dynamic stall. These findings contribute to a better understanding of the flow analysis of morphing aerofoils in an unsteady flow.
| Type de document: | Article publié dans une revue, révisé par les pairs |
|---|---|
| Professeur: | Professeur Botez, Ruxandra Wong, Tony |
| Affiliation: | Génie des systèmes, Génie des systèmes |
| Date de dépôt: | 08 nov. 2023 15:32 |
| Dernière modification: | 14 août 2024 20:18 |
| URI: | https://espace2.etsmtl.ca/id/eprint/27940 |
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