Airfoil Data
NACA662415

The NACA 66(2)-415 is a 9.7% chord-thickness airfoil with a maximum camber of 4.8% 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 -4.8°.

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 slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the NACA662415 typically compare it against profiles of similar thickness: GOE 479 AIRFOIL, GOE 140 (MVA H.17) AIRFOIL, EPPLER 555 AIRFOIL, GOE 174 (ALBATROS 5020) AIRFOIL, GOE 358 AIRFOIL. The NACA 63-209 is another reference profile frequently considered alongside it.