How to check Lift and drag values for a body which has Wing Slats and Flaps?
Please Check the attached images
So I need to check Lift, Drag, Lift-coefficient and Drag coefficient for the model which looks like the above-attached image.
I did name all the three sections as Slat_wall, wing_wall, and Flap_wall respectively and in reference values, I added the area of all the three walls.
Now to check the Lift across the Whole model In results I selected all the three walls (slat, wing, flap) and then checked the force in the Z direction for lift and X direction for Drag, Is it the correct method to calculate lift and drag across the whole model?
Also, Does co-efficient of pressure mean Co-efficient of lift when I'm checking in Z direction?
P.S: All the 3 walls are not attached.