Airfoil Selector

Mass

Speed Unit

Wingspan

Wing Area

m²

Aspect Ratio

MAC Chord (mm)

Fluid Type

Operating Points

How the Selector Works

The selector calculates the required lift coefficient (\$C_L\$) and Reynolds number (\$Re\$) for your specific wing geometry and flight conditions.

$$C_L = \frac{W}{\frac{1}{2} \rho V^2 S}$$

$$Re = \frac{\rho V c}{\mu}$$

Steady Level Flight: Assumes \$L = W\$ (Lift handles total aircraft weight).
Rectangular Simplification: Chord is calculated as $Area / Wingspan$.
Multi-Condition Ranking: Airfoils are ranked by their average performance across all provided operating points.

Speed

Weight

Speed

Weight

Constraints (Optional)

Max Cm

Min moment coefficient threshold (more negative = better stability)

Max Thickness (%)

Maximum thickness as % of chord

Max Camber (%)

Maximum camber as % of chord