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✈️ NACA Airfoil (2D)
NACA 4-Digit Profile
Max Camber M
2%
Camber Position P
0.4c
Thickness T
12%
NACA 2412
Flight Conditions
Angle of Attack α
5°
Airspeed V∞
1.0
⚠ STALL
Live Readout
Lift coeff. Cl
—
Angle of attack α
—
Chord length c
—
Shape from the exact NACA 4-digit parametric equations (thickness distribution + camber line). Lift from thin airfoil theory: Cl = 2π(α − α
L0
).