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May 5, 2021, 05:31 |
Vorticity unexpected results on airfoils
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#1 |
New Member
Join Date: Sep 2020
Posts: 8
Rep Power: 5 |
Hi everyone,
looking at various CFD simulations about airfoils, I have found unexpected visualizations about vorticity, especially on leading edge. I send you here the configuration file and some screenshots about an example (NACA23012, Mach 0.15, Re6e6, AOA 4 deg). The issue presents both with fully turbulent simulations and using BC transition model. I expect to find smoother variation vorticity on leading edge to "link" the positive and negative values of vorticity on upper and lower surfaces. I tried to change CFL and to increase the minimum number of iterations for the RANS, but the results doesn't change a lot. On more complex geometries like multi-element airfoils, reducing the CFL seems to help reducing this unexpected result about vorticity, but the issue presents anyway. May it happens due to 2nd order numerical method? I usually adopt Roe+MUSCL or JST. I would like to understand if I my configuration file is missing something, or understanding if I am ignoring some theoretical aspects, then my judgement about is wrong. Thanks in advance for any kind response. Stefano |
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Tags |
airfoil 2d, su2 7.1.0, vorticity gradient in 2d |
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