Airfoil Data
N63215

The NACA 63-215 AIRFOIL is a 8.5% chord-thickness airfoil with a maximum camber of 4.3% 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 -4.3°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 N63215 appears in the wing design of at least 34 documented aircraft, including designs from Mooney and AviaBellanca. 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 N63215 typically compare it against profiles of similar thickness: GOE 240 (KOLLER) AIRFOIL, MH 70 11.08%, PT40, MH 200 12.97%, S4061-096-84. The NACA 5-H-15 AIRFOIL is another reference profile frequently considered alongside it.