2D NACA0012 airfoil simulation

CFD2018 · May 31, 2018, 16:59

I followed the workshop tutorial to simulate the 2D NACA0012 to simulate compressible flow for Ma=0.7, results looks good.

However, when I reduced the Ma to 0.07, (also make the change to the static pressure and static temperature accordingly) the Cl and Cd is way off compared with data in literature.

Could someone help on it?

Thanks!!

MaelTY · May 31, 2018, 23:15

The reason for this situation may be that， after the flow velocity changes（the Reynolds number changed）, the grid needs to be adjusted. The original turbulence model needs to be reconsidered whether it is appropriate. Even the solver and discrete formats need to be analyzed in depth for new calculations.

May 31, 2018, 16:59	2D NACA0012 airfoil simulation	#1
CFD2018 New Member benz Join Date: May 2018 Posts: 1 Rep Power: 0	I followed the workshop tutorial to simulate the 2D NACA0012 to simulate compressible flow for Ma=0.7, results looks good. However, when I reduced the Ma to 0.07, (also make the change to the static pressure and static temperature accordingly) the Cl and Cd is way off compared with data in literature. Could someone help on it? Thanks!!

May 31, 2018, 23:15	Some suggestions	#2
MaelTY New Member Maël Thomas Join Date: Apr 2018 Posts: 2 Rep Power: 0	The reason for this situation may be that， after the flow velocity changes（the Reynolds number changed）, the grid needs to be adjusted. The original turbulence model needs to be reconsidered whether it is appropriate. Even the solver and discrete formats need to be analyzed in depth for new calculations.

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