Cp values for F3 rear wing for a 4th year thesis

Joe Bryant

Hey,

i am interested to know by setting an area of the aerofoils of a rear wing value in reference areas does that at all interact with calculating the pressure coefficient of say of an 3d aerofoil section.

I noticed that i haven't touch the reference values and i know that when i calculate lift an drag which i will do from the pressure coefficents i have to add the area into it however do i need to do anything to the pressure coeffient (i.e.) incorporate area.

as cp= p -p_inf / (0.5 x density x velocity^2)

also i am only modelling half the rear wing so does that mean that when i calculate lift and drag i only use the area of half the wing (i.e. the two aerofoil elements) and is the area just the reference area of the aerofoil shapes i.e. span x chord. or is it the frontal area, any help would be greatly appreciated. very much so.

cheers joe bryant