Airfoil Data
M20

The NACA M20 AIRFOIL is a 10.2% chord-thickness airfoil with a maximum camber of 5.1% at 30% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.1°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the M20 typically compare it against profiles of similar thickness: GOE 164 (MVA MK.10) AIRFOIL, FX 63-143 AIRFOIL, FX 75-141, NACA M18 AIRFOIL, EPPLER 542 AIRFOIL. The NACA 16-006 is another reference profile frequently considered alongside it.