Airfoil Data
CLARKX

The CLARK X AIRFOIL is a 9.0% chord-thickness airfoil with a maximum camber of 4.5% 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 -4.5°.

Thin airfoil theory predicts a stall angle near 11.8° 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 CLARKX typically compare it against profiles of similar thickness: NACA 16-018, GOE 559 AIRFOIL, USA-35B AIRFOIL, Dormoy, NACA 66-018. The GOE 451 AIRFOIL is another reference profile frequently considered alongside it.