Calculate rear wing downforce and drag based on angle of attack, wing dimensions, and vehicle speed.
Input Parameters
Results
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Wing Area
ft²
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Downforce
lbs
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Drag Force
lbs
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L/D Ratio
Note: Optimal wing angle of attack is typically 6-12 degrees before stall. Higher aspect ratio wings are more efficient (less induced drag). Endplates add 15-30% effectiveness by reducing tip vortices.
Reference
Cl ≈ 2π × sin(α) (thin airfoil theory, inverted)
Cd = Cd0 + Cl² / (π × AR × e)
AR = Span / Chord (aspect ratio)
Downforce = ½ × ρ × V² × Cl × Area
Drag = ½ × ρ × V² × Cd × Area
L/D = Cl / Cd