Airfoil Data
N642415

The NACA 64(2)-415 [NACA 6a series from Theory of Wing Sections] is a 9.6% chord-thickness airfoil with a maximum camber of 4.8% at 40% 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 62 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 N642415 typically compare it against profiles of similar thickness: NACA 64(2)-415, EPPLER 328 AIRFOIL, GOE 796 AIRFOIL, EPPLER E854 AIRFOIL, MH 104 15.28%. The NACA 65(4)-421 is another reference profile frequently considered alongside it.