Aerofoil large AOA
 

Hi Guys,

I am interested i was looking for the reasons why Ansys Fluent struggles to calculate the lift and drag as accurate when the AOA is increased but works fine for lower angles of attack.

The simulation:

The simulation involved analysing a Naca0012 aerofoil at Reynold number of 3 million, the y+ is below 1, the viscous model used was the transition SST (4 equation model). The domain is a C-Grid with 20C behind the aerofoil and 10C above and below.

The simulation was also completed on the Naca4415 aerofoil where fluent over predicted stall, why would this happen?

I have attached a graph of the results obtained for the naca0012 simulations, please if possible inform me of possible problems encountered within my simulation, references would really be appreciated.

Many thanks
Anthony