Airfoil Data
N63010A
NACA 63A010 AIRFOIL
Wing Geometry Simulator
The NACA 63A010 AIRFOIL is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% at 35% 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 -2.5°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 49 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 N63010A appears in the wing design of at least 1 documented aircraft — notably by Douglas. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the N63010A typically compare it against profiles of similar thickness: NACA 64A-010 10.0%, LWK 79-100, RAE 101 AIRFOIL, RAE 100 AIRFOIL, RAE 103 AIRFOIL. The NACA 63(4)-421 is another reference profile frequently considered alongside it.
Aircraft Using the N63010A Airfoil
Douglas D-558-II Skyrocket | Douglas | NACA 63-010 | NACA 63-012 |
Wing lofting: 1 of these aircraft taper from N63010A at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
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AeroSheet loads N63010A airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
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Engineers evaluating the N63010A frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.0%) and max camber (2.5%).
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