Airfoil Data
N12
N-12
Wing Geometry Simulator
The N-12 is a thin 5.3% chord-thickness airfoil with a maximum camber of 2.6% at 30% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -2.6°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 50 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 N12 appears in the wing design of at least 2 documented aircraft — notably by Millicer. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the N12 typically compare it against profiles of similar thickness: MH 23 8%, GIII BL145 AIRFOIL, AG45ct -02f, E10(08%), TsAGI 8% AIRFOIL. The WORTMANN FX 72-MS-150A AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the N12 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.3%) and max camber (2.6%).
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