Airfoil Data
E201
E201 (11.88%)
Wing Geometry Simulator
The E201 (11.88%) is a 8.9% chord-thickness airfoil with a maximum camber of 4.4% 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 -4.4°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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.
The E201 appears in the wing design of at least 1 documented aircraft — notably by JVW/ACM. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the E201 typically compare it against profiles of similar thickness: ARA-D 10% AIRFOIL, NACA 11-H-09 AIRFOIL, EPPLER 58 AIRFOIL, GOE 309 (MVA H.41) AIRFOIL, GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL. The SD7034 is another reference profile frequently considered alongside it.
Aircraft Using the E201 Airfoil
JVW/ACM Industries LAURA | JVW/ACM | Wortmann FX 63-137 | Eppler 201 |
Wing lofting: 1 of these aircraft taper from E201 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the E201 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.9%) and max camber (4.4%).