Airfoil Data
M19

The NACA M19 AIRFOIL is a 9.1% chord-thickness airfoil with a maximum camber of 4.6% at 30% 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 -4.6°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 M19 typically compare it against profiles of similar thickness: S4180-098-84, EPPLER 336 AIRFOIL, NASA/DLR NLF(2)-0415, GOE 617 AIRFOIL, USA 26 AIRFOIL. The NACA 16-006 is another reference profile frequently considered alongside it.