Airfoil Data
NACA2410
NACA 2410
Wing Geometry Simulator
The NACA 2410 is a thin 6.9% chord-thickness airfoil with a maximum camber of 3.4% 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 -3.4°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 55 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 NACA2410 appears in the wing design of at least 5 documented aircraft, including designs from Fiat and Beatty-Johl. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA2410 typically compare it against profiles of similar thickness: GOE 142 (MVA H.19) AIRFOIL, LOCKHEED C-141 BL610.61 AIRFOIL, HQ 3.0/8 AIRFOIL, EPPLER 521 AIRFOIL, GOE 590 AIRFOIL. The NACA 2408 is another reference profile frequently considered alongside it.
Aircraft Using the NACA2410 Airfoil
Beatty-Johl BJ-2 | Beatty-Johl | NACA 65-418 | NACA 2410 mod |
Fiat Aviazione G.50 Freccia | Fiat | NACA 2415 | NACA 2410 |
Fiat Aviazione G.51 | Fiat | NACA 2415 | NACA 2410 |
Fiat Aviazione G.52 | Fiat | NACA 2415 | NACA 2410 |
Toyo TT-10 | Toyo | NACA 1415 | NACA 2410 mod |
Wing lofting: 5 of these aircraft taper from NACA2410 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the NACA2410 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.9%) and max camber (3.4%).