Airfoil Data
NACA4412

The NACA 4412 is a 9.8% chord-thickness airfoil with a maximum camber of 4.9% at 40% 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 -4.9°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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 NACA4412 appears in the wing design of at least 309 documented aircraft, including designs from North American and Aeronca. 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 NACA4412 typically compare it against profiles of similar thickness: AH 79-K-135/20 B, BOEING 106 AIRFOIL, AS6097 | Ananda-Selig | AIAA Paper 2018-0310, EPPLER 546 AIRFOIL, CLARK Z AIRFOIL. The NACA 4415 is another reference profile frequently considered alongside it.