Airfoil Data
N63015A
NACA 63-015A AIRFOIL
Wing Geometry Simulator
The NACA 63-015A AIRFOIL is a thin 7.5% chord-thickness airfoil with a maximum camber of 3.7% at 35% 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 -3.7°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 56 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 N63015A appears in the wing design of at least 12 documented aircraft, including designs from Cicare and Robinson. 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 N63015A typically compare it against profiles of similar thickness: W1015, MH 27 11.99%, FX 71-L-150/30 AIRFOIL, NACA 16-015, E475 (15.01%). The NACA M23 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the N63015A Airfoil
Aviation Industries of Iran AVA-202 | Aviation | NACA 63-215 | NACA 63-015 |
Musger Mg 23 | Musger | NACA 63-015 | Constant |
American Helicopter Company XH-26 | American | NACA 63-015 | Constant |
Cessna CH-1 Skyhook | Cessna | NACA 63-015 | Constant |
Cessna YH-41 Seneca | Cessna | NACA 63-015 | Constant |
Cicare CH-5-AG | Cicare | NACA 63015 | Constant |
Cicare CH-6 | Cicare | NACA 63015 mod | Constant |
Cicare CH-7 | Cicare | NACA 63015 mod | Constant |
Fairchild Hiller FH-1100 | Fairchild | NACA 63-015 | Constant |
Robinson R22 | Robinson | NACA 63-015 | Constant |
Robinson R44 | Robinson | NACA 63-015 | Constant |
Robinson R66 | Robinson | NACA 63-015 | Constant |
Wing lofting: 1 of these aircraft taper from N63015A 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 N63015A frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.5%) and max camber (3.7%).