CFD analysis on blended wing body aircraft for aerodynamic analysis

Im getting high lift coefficient for 5 degree angle of attack and onwards.
The model scaled to half using solidworks & changed the degree of attack in CAD mode…
Im seeking suggestion in order to improve my result.


Perhaps this article can help you:

thanks for the suggestion…
I have went through this previously, but still the results arent good.
one thing to let you know, when I run the simulation for 15 deg AOA … the force and lift coefficient results are not converging.