Airfoil Data
NACA4415

The NACA 4415 is a 11.4% chord-thickness airfoil with a maximum camber of 5.7% at 34% 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.

The NACA4415 appears in the wing design of at least 118 documented aircraft, including designs from Air and Pottier. 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 NACA4415 typically compare it against profiles of similar thickness: FX S 02/1-158 AIRFOIL, NACA M25 AIRFOIL, GOE 406 AIRFOIL, GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL, NN7 MK20. The NACA 4412 is another reference profile frequently considered alongside it.