analyzing using ansys fluent , i considered a 3000 iterations of K-omega turbulent model , but while exporting data , i got the value of cd and cl for each iteration till the end , my question is , which value of cd and cl ill consider at the end ? is it the last iteration value , of at the steady unchanged values ?
Please see the following paper:
https://www.researchgate.net/publication/311276386_THE_EFFECTS_OF_CYLINDER_AT_THE_LEADING_EDGE_OF_AIRFOIL_NACA_0012_ON_THE_BOUNDARY_LAYER_SEPARATION?_iepl%5BviewId%5D=OzDEywmAYRaJQ3TrFqqHjoZ9&_iepl%5BprofilePublicationItemVariant%5D=default&_iepl%5Bcontexts%5D%5B0%5D=prfpi&_iepl%5BtargetEntityId%5D=PB%3A311276386&_iepl%5BinteractionType%5D=publicationTitle
Good luck
Article THE EFFECTS OF CYLINDER AT THE LEADING EDGE OF AIRFOIL NACA ...
Calculate the value once the simulation has reached steady state. Is this a 2d or 3d simulation?? Are you calculating the cd and cl at different attack angles?? You can compare you values with the literature ones for different attack angle values.
Best
Ricardo
Thanks every one for the answers , actually just reached a covered solution as galina said .
Regards
I suggest, try to set all the references values to 1 so to extract the forces in N: in this manner you can have a better feeling of the physical results. You can than calculate the coefficients manually. As Ricardo said, you should check if the coefficient (or directly the monitored force) has become stable. But check also if the residuals of velocity pressure etc have converged (
Also, don't forget to compare your values with the book values from literature as Ricardo suggested.
Please see the following paper:
https://www.researchgate.net/publication/311276386_THE_EFFECTS_OF_CYLINDER_AT_THE_LEADING_EDGE_OF_AIRFOIL_NACA_0012_ON_THE_BOUNDARY_LAYER_SEPARATION?_iepl%5BviewId%5D=OzDEywmAYRaJQ3TrFqqHjoZ9&_iepl%5BprofilePublicationItemVariant%5D=default&_iepl%5Bcontexts%5D%5B0%5D=prfpi&_iepl%5BtargetEntityId%5D=PB%3A311276386&_iepl%5BinteractionType%5D=publicationTitle
Good luck
Article THE EFFECTS OF CYLINDER AT THE LEADING EDGE OF AIRFOIL NACA ...
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