Understand that lift and drag both scale with the square of airspeed and with wing area, but their ratio (L/D — a measure of aerodynamic efficiency) depends only on the lift and drag coefficients.
Lift: L = ½·ρ·V²·A·CLDrag: D = ½·ρ·V²·A·CDL/D = CL / CD (independent of speed and area)Keep the default values (V = 40, A = 20, CL = 1). Confirm the computed lift force exceeds 10,000 N.
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