Airfoil Data
CLARKZ

The CLARK Z AIRFOIL is a 9.8% chord-thickness airfoil with a maximum camber of 4.9% 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 -4.9°.

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 CLARKZ typically compare it against profiles of similar thickness: AS6097 | Ananda-Selig | AIAA Paper 2018-0310, GW 31, GOE 723 AIRFOIL, NACA M15 AIRFOIL, NACA 4412. The USA 26 AIRFOIL is another reference profile frequently considered alongside it.