Airfoil Data
NACA64A410
NACA 64A410
Wing Geometry Simulator
The NACA 64A410 is a thin 7.6% chord-thickness airfoil with a maximum camber of 3.8% at 40% 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 -3.8°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 57 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 NACA64A410 appears in the wing design of at least 5 documented aircraft, including designs from Aviotechnica and Dassault. 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 NACA64A410 typically compare it against profiles of similar thickness: SD8040 (10%), E471 (6.25%), DFVLR R-4 AIRFOIL, WASP (smoothed), MH 106 13.07%. The NACA 64-012A AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA64A410 Airfoil
Aviotechnica Yastreb-2 | Aviotechnica | NACA 64A??? | Constant |
Dassault Falcon 10 | Dassault | NACA (-.8)412.69-62.5 mod ? | NACA 64A(.7)(10.645) mod ? |
Dornier Do 31 | Dornier | NACA 64A412.5 | NACA 64A410 |
Neiva Lanceiro | Neiva | NACA 4410 | NACA 64A410 |
Saab 39 Gripen | Saab | ? | NACA 64A??? |
Wing lofting: 4 of these aircraft taper from NACA64A410 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 NACA64A410 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.6%) and max camber (3.8%).