Airfoil Data
NACA642215
NACA 64(2)-215
Wing Geometry Simulator
The NACA 64(2)-215 is a 8.5% chord-thickness airfoil with a maximum camber of 4.3% at 40% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.3°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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.
Designers evaluating the NACA642215 typically compare it against profiles of similar thickness: NACA 64-215 AIRFOIL, MH 200 12.97%, S4061-096-84, GOE 275 (DAIMLER VI) AIRFOIL, MH 70 11.08%. The NACA 16-021 is another reference profile frequently considered alongside it.
Related Airfoils
Engineers evaluating the NACA642215 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.5%) and max camber (4.3%).