Airfoil Data
WB140

The WB-140/35/FB 14% is a 10.4% chord-thickness airfoil with a maximum camber of 5.2% 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 -5.2°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the WB140 typically compare it against profiles of similar thickness: NACA M23 AIRFOIL, 74-130 WP2, S1221 w/o flap, S1221 w/ 4 deg flap, I.S.A. 960. The RG-12 is another reference profile frequently considered alongside it.