Airfoil Data
NACA66-018
NACA 66-018
Wing Geometry Simulator
The NACA 66-018 is a 9.0% chord-thickness airfoil with a maximum camber of 4.5% at 45% 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 61 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.
Designers evaluating the NACA66-018 typically compare it against profiles of similar thickness: MH 91 14.98%, NACA 16-018, GOE 559 AIRFOIL, USA-35B AIRFOIL, Dormoy. The NACA 64-110 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the NACA66-018 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.0%) and max camber (4.5%).
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