Airfoil Data
E210
E210 (13.64%)
Wing Geometry Simulator
The E210 (13.64%) is a 10.6% chord-thickness airfoil with a maximum camber of 5.3% at 37% 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 -5.3°.
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 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the E210 typically compare it against profiles of similar thickness: GOE 63 AIRFOIL, CURTISS CR-1 AIRFOIL, GOE 493 AIRFOIL, S8037 (16%), GOE 329 (PFALZ 58) AIRFOIL. The GOE 399 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the E210 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.6%) and max camber (5.3%).
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