Airfoil Data
M24

The NACA M24 AIRFOIL is a 12.3% chord-thickness airfoil with a maximum camber of 6.2% at 30% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.2°.

Thin airfoil theory predicts a stall angle near 11.5° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the M24 typically compare it against profiles of similar thickness: FX 67-K-150/17 AIRFOIL, EPPLER 1230 AIRFOIL, NACA M26 AIRFOIL, FX 66-S-171 AIRFOIL, EPPLER 435 AIRFOIL. The NACA 64-108 AIRFOIL is another reference profile frequently considered alongside it.