Airfoil Data
S4233
S4233-136-84
Wing Geometry Simulator
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.
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Engineers evaluating the S4233 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.0%) and max camber (5.0%).
PRANDTL-D-CENTERLINE
Prandtl-D Centerline NASA TP-2016-219072
WB13535SM
WB-135/35 13.5% smoothed
ALTHAUS-AH79K143
AH 79-K-143/18
EPPLER-334
EPPLER 334 AIRFOIL
WORTMANN-FX-79K144
WORTMANN FX 79-K-144/17 AIRFOIL
PRANDTL-D-CENTERLINE
Prandtl-D Centerline NASA TP-2016-219072
WB13535SM
WB-135/35 13.5% smoothed
ALTHAUS-AH79K143
AH 79-K-143/18
EPPLER-334
EPPLER 334 AIRFOIL
WORTMANN-FX-79K144
WORTMANN FX 79-K-144/17 AIRFOIL
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