Airfoil Data
NACA662215
NACA 66(2)-215
Wing Geometry Simulator
The NACA 66(2)-215 is a 8.6% chord-thickness airfoil with a maximum camber of 4.3% at 45% 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 NACA662215 appears in the wing design of at least 11 documented aircraft, including designs from SAIMAN and Caproni. 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 NACA662215 typically compare it against profiles of similar thickness: PSU-90-125WL, NACA 67,1-215, NACA 63(2)-215 MOD B, E193 (10.22%), LOCKHEED L-188 TIP AIRFOIL. The NACA 63-210 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA662215 Airfoil
Caproni Ca.2008 | Caproni | NACA 66-??? | Constant |
Commonwealth CA-15 Kangaroo | Commonwealth | NACA 66-??? | Constant |
General G1-80 Skyfarer | General | NACA ? | Constant |
Hughes D-5 | Hughes | NACA 66-??? | Constant |
Mars M1-80 Skycoupe | Mars | NACA ? | Constant |
Mercury BT-120 Aerobat | Mercury | NACA ? | Constant |
Puritan 50 | Puritan | NACA ? | Constant |
SAIMAN 200 | SAIMAN | NACA | Constant |
SAIMAN 202 | SAIMAN | NACA | Constant |
Somers Kendall SK.1 | Somers | NACA 66-??? | Constant |
Eurofighter Typhoon | Eurofighter | ? | NACA 66-??? |
Wing lofting: 1 of these aircraft taper from NACA662215 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 NACA662215 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.6%) and max camber (4.3%).