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Article Dans Une Revue Journal of Physics: Conference Series Année : 2024

Numerical prediction of aerodynamic loads acting on a blade section-model oscillating in stall

Résumé

For blades operating close to stall angle of attack, one of the potential instabilities is known as stall flutter. It is a dynamic instability in torsion for which the mechanism of energy transfer relies on a dynamic stall process where the flow separates partially or completely during each cycle of oscillation. It leads to dynamic loops in lift, drag and moment that affect the aerodynamic performance of the blade, create unsteady stresses in the blades and can lead to fatigue damage. In the present study, dynamic loops of a NACA 63 4 421 airfoil in forced pitch oscillations have been simulated with the FastS CFD solver based on a URANS modelling approach and compared to benchmark experiments as well as results obtained with the ONERA semi-empirical dynamic stall model using a unique set of dynamic parameters that best fit the experimental dynamic loops. The dynamic tests have been conducted for a mean angle of attack of 13.5°, an amplitude of oscillation of 8° and three reduced frequencies k 1 = 0.0183, k 2 = 0.0785 and k 3 = 0.183. This study has shown that the CFD FastS solver can satisfactorily reproduce the unsteady lift and moment coefficients experienced by a section model oscillating in stall.
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hal-04624700 , version 1 (25-06-2024)

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N Cortes, Xavier Amandolese, Jean Lou Pfister, Frédéric Blondel, R Boisard, et al.. Numerical prediction of aerodynamic loads acting on a blade section-model oscillating in stall. Journal of Physics: Conference Series, 2024, 2767 (2), pp.022014. ⟨10.1088/1742-6596/2767/2/022014⟩. ⟨hal-04624700⟩
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