Airfoil Data
N64215
NACA 64-215 AIRFOIL
Wing Geometry Simulator
The NACA 64-215 AIRFOIL 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.
The N64215 appears in the wing design of at least 11 documented aircraft, including designs from Panstwowe and Ambrosini. 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 N64215 typically compare it against profiles of similar thickness: NACA 64(2)-215, MH 200 12.97%, S4061-096-84, GOE 275 (DAIMLER VI) AIRFOIL, MH 70 11.08%. The NACA 66-018 is another reference profile frequently considered alongside it.
Aircraft Using the N64215 Airfoil
Ambrosini NF 15 | Ambrosini | NACA 64-215 | NACA 64-210 |
General Avia F15F Delfino | General | NACA 64-215 | NACA 64-210 |
Griffon Aerospace Lionheart | Griffon | NACA 64-215 mod | NACA 64-212 mod |
MBB Bo 209 Monsun | MBB | NACA 64-215 | NACA 64-212 |
Monnett Monex | Monnett | NACA 64-215 | Constant |
Panstwowe Zaklady Lotnicze PZL 130 Orlik | Panstwowe | NACA 64-215 | Constant |
Panstwowe Zaklady Lotnicze PZL 140 Orlik 2000 | Panstwowe | NACA 64-215 | Constant |
Procaer F.15 Ficchio | Procaer | NACA 64-215 | NACA 64-210 |
Siegrist RS1 ILSE | Siegrist | NACA 64-215 | Constant |
UTVA Lasta | UTVA | NACA 64-215 | NACA 64-212 |
OMAC 1 | OMAC | NACA 64-215 | NACA 64-212 mod B |
Wing lofting: 7 of these aircraft taper from N64215 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 N64215 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%).