Simulation of dynamic stall for a NACA 0012 airfoil using a vortex method |
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| Institution: | 1. ONERA-DAAA, Paris Saclay University, 92190 Meudon, France;2. Swinburne University of Technology, Hawthorn, Victoria 3122, Australia;3. Fluids Laboratory for Aeronautical and Industrial Research (FLAIR), Department of Mechanical and Aerospace Engineering, Monash University, Melbourne, VIC 3800, Australia;1. Department of Mechanical Engineering, BNMIT, Bangalore 560070, India;2. Department of Mechanical Engineering, PESCE, Mandya 571401, India;3. Department of Mathematics, BNMIT, Bangalore 560070, India;4. NICECFD, Bangalore 560075, India;1. School of Energy and Power Engineering, Xi''an Jiaotong University, Xi''an 710049, China;2. Graduate School of Advanced Technology and Science, Tokushima University, Tokushima 770-8501, Japan |
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| Abstract: | The unsteady, incompressible, viscous laminar flow over a NACA 0012 airfoil is simulated, and the effects of several parameters investigated. A vortex method is used to solve the two-dimensional Navier–Stokes equations in the vorticity/stream-function form. By applying an operator-splitting method, the “convection” and “diffusion” equations are solved sequentially at each time step. The convection equation is solved using the vortex-in-cell method, and the diffusion equation using a second-order ADI finite difference scheme. The airfoil profile is obtained by mapping a circle in the computational domain into the physical domain through a Joukowski transformation. The effects of several parameters are investigated, such as the reduced frequency, mean angle of attack, location of pitch axis, and the Reynolds number. It is observed that the reduced frequency has the most influence on the flow field. |
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