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Lift follows the same form as drag but with the lift coefficient: L = 0.5 rho v^2 Cl A. A 16 m2 wing at Cl 1.2 and 45 m/s generates about 23.8 kN, enough to hold 2430 kg aloft. Since lift goes with speed squared, halving speed quarters lift - which is why stall speed rises with weight and falls with air density.
Lift force
L = 0.5 x rho x v^2 x Cl x A
Dynamic pressure
q = 0.5 rho v^2
Because air density falls, so the same lift requires a higher true airspeed. Indicated airspeed, which measures dynamic pressure, stays the same.
Stall. Beyond roughly 15 degrees of angle of attack the flow separates and Cl collapses; flaps and slats push the usable maximum higher.