Main article: XHTTPX//en.wikipedia.org/wiki/Lift_coefficient
If the lift coefficient for a wing at a specified angle of attack is known (or estimated using a method such as XHTTPX//en.wikipedia.org/wiki/Thin-airfoil_theory), then the lift produced for specific flow conditions can be determined using the following equation:
where
L is lift force,
ρ is air XHTTPX//en.wikipedia.org/wiki/Density
v is XHTTPX//en.wikipedia.org/wiki/True_airspeed,
A is XHTTPX//en.wikipedia.org/wiki/Planform area, and
CL is the lift coefficient at the desired angle of attack, XHTTPX//en.wikipedia.org/wiki/Mach_number, and XHTTPX//en.wikipedia.org/wiki/Reynolds_number
