Airfoil Data
CLARYM15

The CLARK YM-15 AIRFOIL is a 10.9% chord-thickness airfoil with a maximum camber of 5.4% 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 -5.4°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the CLARYM15 typically compare it against profiles of similar thickness: GOE 15K AIRFOIL, GOE 619 AIRFOIL, NACA 2418, GOE 497 AIRFOIL, GOE 319 (HANSA-BRANDENBURG II) AIRFOIL. The FX 66-17AII-182 AIRFOIL is another reference profile frequently considered alongside it.