Airfoil Data
GOE449
GOE 449 AIRFOIL
Wing Geometry Simulator
The GOE 449 AIRFOIL is a 13.8% chord-thickness airfoil with a maximum camber of 6.9% at 40% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.9°.
Thin airfoil theory predicts a stall angle near 11.0° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE449 appears in the wing design of at least 2 documented aircraft, including designs from Alcione and Bonomi. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE449 typically compare it against profiles of similar thickness: S1223 RTL, MH 113 14.62%, NACA 2424, GOE 255 (MVA CA.6) AIRFOIL, SP4721BS. The WORTMANN FX 71-089A AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE449 Airfoil
Alcione BS 28 | Alcione | Goettingen 449 | NACA 0012 |
Bonomi BS.28 Alcione | Bonomi | Goettingen 449/693 | NACA 23012/0012 |
Wing lofting: 2 of these aircraft taper from GOE449 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 GOE449 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.8%) and max camber (6.9%).