What would be the lift formula for straight wings? I have been trying to estimate the lift calculation for a straight wing. The previous project I worked on was a swept wing. But this is a straight wing. I would like to to get the stall speed so I need the Clmax formula. What would the lift formula for this type of wing be?
Regardless of the geometrical shape of the wing, you need to know the wing area to determine the lift force as it is one of the factors that affect lift.

Calculate lift using this formula: $$Lift = \frac{1}{2} (C_L * P * S * V^2)$$.


$C_L$: coefficient of lift
$P$: density of air
$S$: surface area of the wing
$V$: velocity of air