Airfoil Data
NACA0010
NACA 0010
Wing Geometry Simulator
The NACA 0010 is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% 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 -2.5°.
Thin airfoil theory predicts a stall angle near 11.9° 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 NACA0010 appears in the wing design of at least 30 documented aircraft, including designs from Boeing and Avro. 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 NACA0010 typically compare it against profiles of similar thickness: HQ 0/10 AIRFOIL, RAE 102 AIRFOIL, NACA 0010-64, NACA 0010-65, NASA SC(2)-0710 AIRFOIL. The NACA 0010-65 is another reference profile frequently considered alongside it.
Aircraft Using the NACA0010 Airfoil
AL 3 Olimpico | AL | NACA 5514 | NACA 0010 |
Avro 698 Vulcan | Avro | NACA 0010 mod | NACA 0008 mod |
Avro 707 | Avro | NACA 0010 mod | Constant |
Avro Canada CF-100 Canuck | Avro | NACA 0010 | Constant |
Blohm & Voss Bv 238 | Blohm | NACA 0020 ? | NACA 0010 ? |
Boeing 294 XB-15 | Boeing | NACA 0018 | NACA 0010 |
Boeing 294 XBLR-1 | Boeing | NACA 0018 | NACA 0010 |
Boeing 294 XC-105 | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 B-17 Flying Fortress | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 B-40 Flying Fortress | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 BQ-7 | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 F-9 | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 PB-1 | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 XB-38 | Boeing | NACA 0018 | NACA 0010 |
Boeing 299 XC-108 | Boeing | NACA 0018 | NACA 0010 |
Boeing 307 Stratoliner (C-75) | Boeing | NACA 0018 | NACA 0010 |
Boeing 314 Clipper (C-98) | Boeing | NACA 0018 | NACA 0010 |
Caproni Campini N.1 | Caproni | NACA 0019 | NACA 0010 ? |
Curtiss SO2C | Curtiss | NACA 0010 (upper) | NACA 2212 (lower) |
Curtiss SOC Seagull | Curtiss | NACA 0010 (upper) | NACA 2212 (lower) |
Wing lofting: 26 of these aircraft taper from NACA0010 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 NACA0010 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%).