Airfoil Data
GOE527
GOE 527 AIRFOIL
Wing Geometry Simulator
The GOE 527 AIRFOIL is a 13.9% chord-thickness airfoil with a maximum camber of 7.0% at 29% 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 -7.0°.
Thin airfoil theory predicts a stall angle near 10.9° 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 GOE527 appears in the wing design of at least 3 documented aircraft, including designs from Akaflieg and Avia. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE527 typically compare it against profiles of similar thickness: GOE 711 AIRFOIL, RAF 89 AIRFOIL, GOE 226 (MVA H.36) AIRFOIL, Dayton-Wright 6, FX 76-MP-160. The DAE-51 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE527 Airfoil
Akaflieg Stuttgart F.1 | Akaflieg | Goettingen 535 | Goettingen 527 |
Avia 41P | Avia | Goettingen 535 | Goettingen 527 |
Klemm L20 | Klemm | Goettingen 527 | Goettingen 529 |
Wing lofting: 3 of these aircraft taper from GOE527 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 GOE527 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.9%) and max camber (7.0%).