Airfoil Data
NACA001064
NACA 0010-64
Wing Geometry Simulator
The NACA 0010-64 is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% 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 -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 NACA001064 appears in the wing design of at least 3 documented aircraft, including designs from Martin and Northrop. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA001064 typically compare it against profiles of similar thickness: HQ 0/10 AIRFOIL, RAE 102 AIRFOIL, NACA 0010-65, NASA SC(2)-0710 AIRFOIL, RAE 104 AIRFOIL. The LOCKHEED L-188 TIP AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA001064 Airfoil
Martin 179 B-26 Marauder | Martin | NACA 0017-64 | NACA 0010-64 |
Martin 182 XB-27 | Martin | NACA 0017-64 | NACA 0010-64 |
Northrop X-4 Bantam | Northrop | NACA 0010-64 | Constant |
Wing lofting: 2 of these aircraft taper from NACA001064 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 NACA001064 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%).