Airfoil Data
GOE497
GOE 497 AIRFOIL
Wing Geometry Simulator
The GOE 497 AIRFOIL is a 10.9% chord-thickness airfoil with a maximum camber of 5.4% at 40% 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 -5.4°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 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.
The GOE497 appears in the wing design of at least 1 documented aircraft — notably by Akaflieg. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE497 typically compare it against profiles of similar thickness: NACA 2418, GOE 319 (HANSA-BRANDENBURG II) AIRFOIL, GOE 619 AIRFOIL, GOE 15K AIRFOIL, CLARK YM-15 AIRFOIL. The RAF 15 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE497 Airfoil
Akaflieg Berlin B 5 | Akaflieg | Goettingen 549 | Goettingen 497 |
Wing lofting: 1 of these aircraft taper from GOE497 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 GOE497 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.9%) and max camber (5.4%).