What would be the lift formula for straight wings?
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