CFD Online Discussion Forums - How to obtain coefficient of lift and drag of airfoil at specified angle of attack

Dear experts,

I am simulating a 2D/3D airfoil at an angle of attack of 7 degree, and trying to find the coefficient of lift and drag by writing a function in controlDic, although there are no errors but the results looks very off from the measured data, could anyone please help me with these confusions:
1. For an angle of attack 7 degree, what would be the values of

Code:

liftDir

and

Code:

dragDir

?
For zero angle of attack I guess these will be

Code:

liftDir (0 1 0 )

and

Code:

dragDir (1 0 0)

2. What would be the

Code:

Aref

if I have an airfoil of chord length 1 meter and extruded 1 m in the spanwise length, I assume the

Code:

Aref 1 ?

. Will this be same if I am performing 2D or 3D simulations ?

3. Is there any way to obtain these coefficients after the simulations as postProcessing ?

For getting the 7 angle of attack I am rotating the airfoil. Any suggestion/comment will be a great help, thanks in advance.