Airfoil Data
GOE416A
GOE 416A AIRFOIL
Wing Geometry Simulator
The GOE 416A AIRFOIL is a thin 6.7% chord-thickness airfoil with a maximum camber of 3.3% at 29% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.3°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 GOE416A appears in the wing design of at least 3 documented aircraft, including designs from Kawanishi and Latham. 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 GOE416A typically compare it against profiles of similar thickness: E224 (10.17%), HQ 2.1/9.5 AIRFOIL, GOE 54 AIRFOIL, SIKORSKY SC2110 AIRFOIL, NASA/LANGLEY RC-10(B)3 AIRFOIL. The HQ 2.5/9.0 smoothed by Eppler is another reference profile frequently considered alongside it.
Aircraft Using the GOE416A Airfoil
Kawanishi K-11 | Kawanishi | Goettingen 420 (upper) | Goettingen 416 (lower) |
Latham L-2 | Latham | Goettingen 416 | Constant |
Nieuport-Delage Sesquiplan | Nieuport-Delage | Goettingen 416 | Constant |
Wing lofting: 1 of these aircraft taper from GOE416A 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 GOE416A frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.7%) and max camber (3.3%).