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September 8, 2009, 04:58 |
Multi-Body Airfoil simulation problems
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#1 |
Senior Member
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Hi Foamers,
I'm trying to simulate the flow around a 2D high lift configuration airfoil (slat - main - flap), Re=6x10^6, Ma=0.2, AoA = 12.2°, with simpleFoam, k-Omega SST turbulence. I tryied both high Re mesh type, so yPlusMin > 30, and Low Re mesh type, so yPlusMax < 1, as in OF 1.6 it's possible to switch off the wall-functions in SSt model. My boundary condition are: Far field: U - inletOutlet p - inletOutlet k - turbulentIntensityKineticEnergyInlet Omega - turbulentMixingLengthFrequencyInlet Walls with yPlus > 30 U - fixedValue (0 0 0) p - zeroGradient k - kqRWallFunction Omega - omegaWallFunction Walls with yPlus < 1 U - fixedValue (0 0 0) p - zeroGradient k - fixedValue 0 Omega - omegaWallFunction I used the standard best-practise to get the solution, so starting with upwind schemes at the beginning and then 2° order Gamma schemes, playing with the relaxation factors to make it converge, and I get a stable solution. My fvSchemes and fvSolution are attached. The results are like this: U P k cp The cp values are completely incorrect, as the reference solution for this case has a negative peak of around -4 near the main, and a cp of about -2 / -2.5 on the main upper surface. Does anyone have some idea to get better results? I'm struggling on it from weeks... Have a nice day! |
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