Airfoil Data
NACA632A015

The NACA 63(2)A-015 is a 8.8% chord-thickness airfoil with a maximum camber of 4.4% at 34% 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 -4.4°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 NACA632A015 appears in the wing design of at least 4 documented aircraft, including designs from Breguet and Beech. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the NACA632A015 typically compare it against profiles of similar thickness: GOE 134 (MVA H.12) AIRFOIL, Apex 16 (normalized using XFOIL date021206), RONCZ LOW DRAG FLYING WING AIRFOIL, PSU 94-097 (AIAA 2001-2478), RAF 32 MOD AIRFOIL. The NACA M20 AIRFOIL is another reference profile frequently considered alongside it.