Airfoil Data
N63415

The NACA 63-415 AIRFOIL is a 9.6% chord-thickness airfoil with a maximum camber of 4.8% at 35% 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 -4.8°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 62 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.

The N63415 appears in the wing design of at least 23 documented aircraft, including designs from FFA and Potez. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the N63415 typically compare it against profiles of similar thickness: EPPLER 393 AIRFOIL, SOKOLOV AIRFOIL, EPPLER STE 871-514 AIRFOIL, ONERA OA213 AIRFOIL, EPPLER 407 AIRFOIL. The NACA 65-209 is another reference profile frequently considered alongside it.