Airfoil Data
NACA633218
NACA 63(3)-218
Wing Geometry Simulator
The NACA 63(3)-218 is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 35% 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 -5.0°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The NACA633218 appears in the wing design of at least 2 documented aircraft, including designs from Hughes and Hughes-Kaiser. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA633218 typically compare it against profiles of similar thickness: MARSKE XM-1D AIRFOIL (F14-3.0), NACA 64(3)-218, GOE 81 AIRFOIL, LA2573A, GOE 7K AIRFOIL. The NACA M8 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA633218 Airfoil
Hughes H-4 Hercules | Hughes | NACA 63(420)-321 | NACA 65(420)-415 |
Hughes-Kaiser HK-1 Hercules | Hughes-Kaiser | NACA 63(420)-321 | NACA 65(420)-415 |
Wing lofting: 2 of these aircraft taper from NACA633218 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 NACA633218 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.0%) and max camber (5.0%).