Airfoil Data
GOE435
GOE 435 AIRFOIL
Wing Geometry Simulator
The GOE 435 AIRFOIL is a thick 16.7% chord-thickness airfoil with a maximum camber of 8.3% at 28% 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 -8.3°.
Thin airfoil theory predicts a stall angle near 10.0° and a peak lift-to-drag ratio around 75 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 17% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE435 appears in the wing design of at least 1 documented aircraft — notably by Latecoere. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE435 typically compare it against profiles of similar thickness: MH 150 23.89%, GOE 390 AIRFOIL, St. CYR 234 (Bartel 17-IC), TH 25816 HALE AIRFOIL, FX74_CL5_140. The EPPLER 908 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE435 Airfoil
Latecoere 14 | Latecoere | Goettingen 435 | Goettingen 430 |
Wing lofting: 1 of these aircraft taper from GOE435 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 GOE435 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (16.7%) and max camber (8.3%).