Airfoil Data
E193
E193 (10.22%)
Wing Geometry Simulator
The E193 (10.22%) is a 8.6% chord-thickness airfoil with a maximum camber of 4.3% 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 -4.3°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 E193 typically compare it against profiles of similar thickness: NACA 67,1-215, NACA 63(2)-215 MOD B, EPPLER 635 AIRFOIL, PSU-90-125WL, NACA 66(2)-215. The NASA/LANGLEY RC-10(N)1 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the E193 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.6%) and max camber (4.3%).
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