Airfoil Data
S4233

The S4233-136-84 is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 35% 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 -5.0°.

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 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the S4233 typically compare it against profiles of similar thickness: Prandtl-D Centerline NASA TP-2016-219072, WB-135/35 13.5% smoothed, AH 79-K-143/18, EPPLER 334 AIRFOIL, WORTMANN FX 79-K-144/17 AIRFOIL. The GOE 683 AIRFOIL is another reference profile frequently considered alongside it.