Airfoil Data
NACA65209
NACA 65-209
Wing Geometry Simulator
The NACA 65-209 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 NACA65209 appears in the wing design of at least 2 documented aircraft, including designs from Foxjet and McDonnell. 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 NACA65209 typically compare it against profiles of similar thickness: RAF 15 AIRFOIL, NLR-1T AIRFOIL, AG54, NACA 64-209, SIKORSKY SSC-A09 AIRFOIL. The NACA 63-415 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA65209 Airfoil
Foxjet 600 | Foxjet | NACA 65-???? | Constant |
McDonnell F2H Banshee | McDonnell | NACA 65-212 | NACA 65-209 |
Wing lofting: 1 of these aircraft taper from NACA65209 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 NACA65209 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%).