Airfoil Data
NACA0008
NACA 0008
Wing Geometry Simulator
The NACA 0008 is a thin 4.0% chord-thickness airfoil with a maximum camber of 2.0% 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 -2.0°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 47 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 NACA0008 appears in the wing design of at least 1 documented aircraft — notably by Avro. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA0008 typically compare it against profiles of similar thickness: S9027 (8%), NACA 0008-34, NACA M2 AIRFOIL, NACA 64-008A AIRFOIL, FX 77-080. The NACA 0018 is another reference profile frequently considered alongside it.
Aircraft Using the NACA0008 Airfoil
Avro 698 Vulcan | Avro | NACA 0010 mod | NACA 0008 mod |
Wing lofting: 1 of these aircraft taper from NACA0008 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 NACA0008 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (4.0%) and max camber (2.0%).