Airfoil Data
NACA001034A08CLI0.2
NACA 0010-34 a=0.8 c(li)=0.2
Wing Geometry Simulator
The NACA 0010-34 a=0.8 c(li)=0.2 is a thin 6.3% chord-thickness airfoil with a maximum camber of 3.1% 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 -3.1°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 53 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 NACA001034A08CLI0.2 appears in the wing design of at least 1 documented aircraft — notably by Amin. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA001034A08CLI0.2 typically compare it against profiles of similar thickness: RAE6-9CK AIRFOIL, KC-135 Winglet (supercritical Whitcomb), RAE 2822 AIRFOIL, NACA 64A210, BOEING 707 .99 SPAN AIRFOIL. The NACA 0012-64 a=0.8 c(li)=0.2 is another reference profile frequently considered alongside it.
Aircraft Using the NACA001034A08CLI0.2 Airfoil
Amin Gepal Mk IV 550 | Amin | NACA 230?? | NACA 00?? |
Wing lofting: 1 of these aircraft taper from NACA001034A08CLI0.2 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 NACA001034A08CLI0.2 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.3%) and max camber (3.1%).