[Vincentsalome]

Hi all,

I am doing n small piece of research where I want to validate the use of the squire young model for drag prediction (as used in XFOIL).

I am running XFOIL simulations in a region of verified accuracy with respect to wind tunnel results and then want to evaluate the differences between the XFOIL calculated drag, the star ccm + drag and the drag calculated from the Squire-Young model with parameter inputs as calculated from star simulation.

If you are not familiar with the Squire-Young model, it uses inputs of edge velocity at wake end, shape parameter, freestream velocity, momentum thickness and shape parameter.

As I am not a star ccm+ veteran I need help to extract the values of the displacement thickness and momentum thickness from my 2d airfoil simulation.

Thanks in advance.

[fluid23]

Create a point on the airfoil surface where you want to find your thickness then create a local coordinate system that is normal to the surface. Finally, create a derived part and a threshold to extract velocity profiles.

Then you will have to integrate to get momentum and displacement thickness.

Here is a link that may be helpful. Not exactly what you are trying to do, but gets you close.
https://community.plm.automation.sie...es/ba-p/434180