Joukowski Airfoil
Circle center x₀:
-0.15
Circle center y₀:
0.12
Transform param λ:
1.0
Attack angle α:
5°
Flow speed V:
1.0
Streamlines N:
20
Toggle: Circle/Airfoil
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Lift coeff CL =
—
Γ (circulation) =
—
Joukowski transform: w = z + λ²/z maps circle → airfoil. Kutta condition: set circulation so rear stagnation point is at trailing edge. CL = 2πα (thin airfoil theory).