Airfoil Data
N2414

The NACA 2414 is a 8.9% chord-thickness airfoil with a maximum camber of 4.5% 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 -4.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 N2414 appears in the wing design of at least 11 documented aircraft, including designs from Caproni and Akaflieg. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the N2414 typically compare it against profiles of similar thickness: AS6096 | Ananda-Selig | AIAA Paper 2018-0310, EPPLER 58 AIRFOIL, LOCKHEED L-188 ROOT AIRFOIL, APEX 16, ARA-D 10% AIRFOIL. The NACA 2415 is another reference profile frequently considered alongside it.