Airfoil Data
M25

The NACA M25 AIRFOIL is a 11.4% chord-thickness airfoil with a maximum camber of 5.7% 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 -5.7°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the M25 typically compare it against profiles of similar thickness: GOE 406 AIRFOIL, GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL, NACA 4415, FX S 02/1-158 AIRFOIL, FX 61-168 AIRFOIL. The NACA M13 AIRFOIL is another reference profile frequently considered alongside it.