Airfoil Data
M15

The NACA M15 AIRFOIL is a 9.8% chord-thickness airfoil with a maximum camber of 4.9% 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 -4.9°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the M15 typically compare it against profiles of similar thickness: GOE 723 AIRFOIL, GW 31, GOE 738 AIRFOIL, MRC12, BOEING 103 AIRFOIL. The NACA 65-209 is another reference profile frequently considered alongside it.