[mazhar16823]

Hi everyone,


I have conducted 3D simulations for two airfoils by using Transition SST Gamma_ReTheta model as both of the airfoil undergo angle of attack between 4 and 8 degrees. The results obtained are very disappointing, as my goal is to determine the location of transition on these two sections (which I did in 3D blade and it worked). But for these airfoils, skin friction coefficient and pressure coefficient plots provide exaggerated view of the data and even until 3000 iterations drag coefficient experiences fluctuations.



I am using steady, segregated flow, Transition SST K-Omega+Gamma ReTheta. Further, I have attached the figures for your perusal. I would highly appreciate your suggestions in this regard.





Regards,