NUMERICAL SIMULATION OF SUBSONIC TURBULENT FLOW OF OSCILLATING NACA 0015 AIRFOIL
DOI:
https://doi.org/10.32782/2618-0340-2018-2-133-145Keywords:
oscillating aerodynamic airfoil, Navier-Stokes equations, turbulence model, flow separationAbstract
The results of calculations of the oscillating NACA 0015 airfoil for three flow regimes are presented: a weak flow separation corresponding to an average angle of attack of 4°; developed separation – 11° (subcritical flow around the airfoil); massive separation – 15° (supercritical flow around the airfoil). The authors have developed a specialized CFD package in which a compromise between the required computational resources and the quality of the results. On the one hand, provide a complete approach of computational fluid dynamics based on the Navier-Stokes equations, including several differential turbulence models, as well as multi-block approach for the flows in multiply connected domains. Designed CFD package allows us to solve the problem of dynamics and aerodynamics, including electrodynamics processes, electrochemistry, multiphase fluids, combustion processes and plasma kinetics. For the numerical simulation of the flow around an oscillating airfoil, Reynolds-averaged unsteady Navier-Stokes equations of an incompressible fluid closed by a one-parameter turbulent viscosity model are used. The developed implicit finitevolume numerical algorithm is based on the method of artificial compressibility modified for the calculation of unsteady tasks. Visualization of turbulent flow around oscillating NACA 0015 airfoil is obtained. The obtained fields of vorticity, instantaneous streamlines, and hysteresis curves of unsteady aerodynamic loads of the airfoil are analyzed for three characteristic flow regimes. The stages of generation, development and stalling of vortices are described in the flow around oscillating NACA 0015 airfoil. The developed technique makes it possible to reproduce the structure of an unsteady separated flow around an oscillating airfoil. The differences in the aerodynamic characteristics of the stationary and oscillating airfoils at the same angles of attack are in good agreement with the experimental data. Comparison of the computational results of a flow around an oscillating airfoil with experimental data and known calculations by other authors showed the advantage of the SALSA turbulence model compared to other tested models, especially in the presence of massive flow separation.
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