Airfoil Data
DU8608418

The DU86-084/18 8.44% is a thin 5.3% chord-thickness airfoil with a maximum camber of 2.7% at 37% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -2.7°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 50 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 DU8608418 typically compare it against profiles of similar thickness: M6 (65%), GIII BL207 AIRFOIL, GIII BL167 AIRFOIL, NACA M4 AIRFOIL, TsAGI 8% AIRFOIL. The GOE 314 (HANSA-BRANDENBURG) AIRFOIL is another reference profile frequently considered alongside it.