Airfoil Data
N10

The N-10 is a 11.2% chord-thickness airfoil with a maximum camber of 5.6% 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 -5.6°.

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 N10 typically compare it against profiles of similar thickness: DAI 1238, GOE 655 AIRFOIL, FX 84-W-140, FX 63-145 AIRFOIL, GOE 29B AIRFOIL. The NACA 4424 is another reference profile frequently considered alongside it.