>>11146286Okay, so basically what you are asking for is "What is the coefficient of lift and drag for this shape?" The definitions of these coefficients are below:
Drag coefficient = Drag force / (dynamic pressure × horizontally projected area)
Lift coefficient = Lift force / (dynamic pressure × vertically projected area)
The answer is that it is hard to determine from first principles. In practice, engineers use simulations and wind tunnel experiments to find these coefficients as a function of angle of attack.
Theoretically, you would use the theory of boundary layers to find momentum thickness, displacement thickness, shape factor, etc., then you would apply newton's laws to find the pressure differential over the wing and the shear stresses on the surface of the wing which give you lift and drag, respectively.
