Airfoil Data
NACA64209
NACA 64-209
Wing Geometry Simulator
The NACA 64-209 is a thin 5.6% chord-thickness airfoil with a maximum camber of 2.8% 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 -2.8°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 51 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 NACA64209 appears in the wing design of at least 3 documented aircraft, including designs from Kaminskas and Panstwowe. 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 NACA64209 typically compare it against profiles of similar thickness: AG54, NLR-1T AIRFOIL, SIKORSKY SSC-A09 AIRFOIL, RAF 15 AIRFOIL, NACA 65-209. The NACA 65-206 is another reference profile frequently considered alongside it.
Aircraft Using the NACA64209 Airfoil
Kaminskas Jungster III | Kaminskas | NACA 64-212 | NACA 64-209 |
Panstwowe Zaklady Lotnicze PZL Mielec TS-11 Iskra | Panstwowe | NACA 64-209 | NACA 64-009 |
Siersma SRC-1 | Siersma | NACA 64-209 | Constant |
Wing lofting: 2 of these aircraft taper from NACA64209 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 NACA64209 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.6%) and max camber (2.8%).