Airfoil Data
N63412
NACA 63-412 AIRFOIL
Wing Geometry Simulator
The NACA 63-412 AIRFOIL is a 8.1% chord-thickness airfoil with a maximum camber of 4.0% at 40% 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 -4.0°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 N63412 appears in the wing design of at least 10 documented aircraft, including designs from Luscombe and AerMacchi. 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 N63412 typically compare it against profiles of similar thickness: GOE 495 AIRFOIL, AH 79-100 A AIRFOIL, GOE 673 AIRFOIL, EPPLER E837 HYDROFOIL AIRFOIL, GOE 410 AIRFOIL. The NACA 66-210 is another reference profile frequently considered alongside it.
Aircraft Using the N63412 Airfoil
Aermacchi M-290TP Redigo | AerMacchi | NACA 63-218(mod B3) | NACA 63-412(mod B3) |
Dempsey TD-162 | Dempsey | NACA 63-412 | Constant |
Freedom Transports FTI300 | Freedom | NACA 63-412 | Constant |
Hurel-Dubois HDM.105 | Hurel-Dubois | NACA 63-420 | NACA 63-412 |
Luscombe Aircraft P3 Rattler | Luscombe | NACA 63-412 | Constant |
Luscombe Aircraft Valiant | Luscombe | NACA 63-412 | Constant |
Miles HDM.105 | Miles | NACA 63-420 | NACA 63-412 |
Oberlerchner JOB 15 | Oberlerchner | NACA 64-418 | NACA 63-412 |
Thorp T-18 | Thorp | NACA 63-412 | Constant |
Valmet L-90 Redigo | Valmet | NACA 63-218(mod B3) | NACA 63-412(mod B3) |
Wing lofting: 5 of these aircraft taper from N63412 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 N63412 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.1%) and max camber (4.0%).