Abstract
Dynamic stall phenomenon on a Boeing Vetrol-VR-7 airfoil, oscillating at quarter chord with reduced frequency of 0.1, is investigated at three different slot configurations—leading edge, trailing edge and combination of this two edges at a Reynolds number of 2.5 × 106. It is shown that the use of a leading-edge slot can eliminate the dynamic stall vortex (DSV) and increase the lift coefficient by 20%, and a decrease in the drag and moment coefficient by more than 70%. It is computed that the performance at low angles of attack can be improved with the use of a non-drooped leading edge in the airfoil. Furthermore, the combination of a leading and trailing-edge slots further improves the lift characteristics.
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Ramana, P.B.L.V., Paul, A.R., Jain, A., Matsuura, K. (2021). Computational Study on Dynamic Stall and Flow Control in a Pitching Airfoil. In: Venkatakrishnan, L., Majumdar, S., Subramanian, G., Bhat, G.S., Dasgupta, R., Arakeri, J. (eds) Proceedings of 16th Asian Congress of Fluid Mechanics. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-5183-3_1
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