where

L is lift force,
ρ is air density
v is true airspeed,
A is planform area, and
CL is the lift coefficient at the desired angle of attack, Mach number, and Reynolds number

Also,

where:

L is the lift,
A is the wing surface area
p is the value of the pressure,
n is the normal unit vector pointing into the wing, and
k is the vertical unit vector, normal to the freestream direction.