Airfoil Data
NACACYH

The NACA CYH is a 11.7% chord-thickness airfoil with a maximum camber of 5.9% 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 -5.9°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 68 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the NACACYH typically compare it against profiles of similar thickness: EPPLER 552 AIRFOIL, GOE 398 AIRFOIL, USA 27 mod. AIRFOIL, Curtis C-72, GOE 431 AIRFOIL. The NACA M15 AIRFOIL is another reference profile frequently considered alongside it.