[Alhasan]

Hello Everyone,

For a three element airfoil, there are three elements, how do I get my Cl and Cd from openFOAM do I consider them as induvidual airfoils or what ? any suggestions ? I have attached an Image of 30P30N airfoil.


I have been playing with this airfoil for past 2 weeks, I am not able to get the Cp Distribution around the Slat accurately, the results are off only for the slat on the lower surface !! This is due to the recirculation flow that is on the lower surface of the slat which is not suposed to be at such high velocity in there, I have tried wallfunctions and also withoutwall functions and Y+ = 1,

any suggestions as to why the flow on the lowerside of the slat is accelerating to high velocity on the left side after the impingement ? It is not suposed to accelerate to such velocity within the slat cove.

How should I determine the Y distance for these types of flows any suggestions?

Thanks for your time and inputs

Kind Regards,
Hasan K.J

[tareqkh]

Hello Alhasan,

I believe that you have to make three forcecoeff functions with different names such as forcecoeff1, forcecoeff2, and forcecoeff3 and change each patch to your airfoil. Finally, type # include
" your functions into your controldict". I hope this might help.