Lift force and Drag force calculation
 

Hi all,
This is my first post over here. For my MS thesis, I am working on a Clark Y aerofoil with experimental approach using an AEROLAB educational wind tunnel. I have set the problem in STAR CCM+ replicating the exact conditions in the wind tunnel. I did the run the simulations with good results showing the overall velocity and pressure profile.
Now, I need to extract exact forces acting on the upper and lower surface of the aerofoil [I have already divided the surfaces into two different regions]. I have no idea how to go about it. How can I extract this particular data from the simulation? I need both normal and axial forces to calculate lift and drag forces and subsequently their coefficients.
Any help is highly appreciated. I have very little experience with STAR CCM+.

Hi!
Bring up the following in the the help section:
Tutorial Guide > Compressible Flow > Transonic Flow: RAE2822 Airfoil
Following the tutorial through should help :-)

Hi, there is a folder on the left where it is written "reports" just right click on it and select Force report or Force coefficient...here you will find various parameters to be set e.g. the normal vector where the integration of pressure forces and shear forces will be projected, the region where the software will perform the integration and so on...
any way in the manual under the "tutorials" section you can find some examples!

I'm sorry, I'm late with my Thank You note. Thanks, DaveyBaby, your input helped alot. :)
Hello Micheal, thanks for your help. I followed the tutorial referred to earlier in the thread and got to the 'reports'!:)