Agradecimentos: CENAPAD-SP [551]; US Air Force Office of Scientific ResearchUnited States Department of DefenseAir Force Office of Scientific Research (AFOSR) [FA9550-18-1-0040]

High-fidelity simulations are performed to study active flow control techniques for alleviating deep dynamic stall of an SD7003 airfoil in plunging motion. The flow Reynolds number is Re = 60 000 and the freestream Mach number is M = 0.1. Numerical simulations are performed with a...

High-fidelity simulations are performed to study active flow control techniques for alleviating deep dynamic stall of an SD7003 airfoil in plunging motion. The flow Reynolds number is Re = 60 000 and the freestream Mach number is M = 0.1. Numerical simulations are performed with a finite-difference-based solver that incorporates high-order compact schemes for differentiation, interpolation, and filtering on a staggered grid. A mesh convergence study is conducted and results show good agreement with available data in terms of aerodynamic coefficients. Different spanwise arrangements of actuators are implemented to simulate blowing and suction at the airfoil leading edge. We observe that, for a specific frequency range of actuation, mean drag and drag fluctuations are substantially reduced while mean lift is maintained almost unaffected, especially for a two-dimensional (2D) actuator setup. For this frequency range, 2D flow actuation disrupts the formation of the dynamic stall vortex, which leads to drag reduction due to a pressure increase along the airfoil suction side, towards the trailing edge region. At the same time, pressure is reduced on the suction side near the leading edge, increasing lift and further reducing drag

FUNDAÇÃO DE AMPARO À PESQUISA DO ESTADO DE SÃO PAULO - FAPESP

2013/08293-7; 2013/07375-0; 2016/245046; 2018/04210-3

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