Airfoil Data
GOE290
GOE 290 (MVA 290) AIRFOIL
Wing Geometry Simulator
The GOE 290 (MVA 290) AIRFOIL is a 12.5% chord-thickness airfoil with a maximum camber of 6.2% 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 -6.2°.
Thin airfoil theory predicts a stall angle near 11.4° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE290 appears in the wing design of at least 2 documented aircraft, including designs from Junkers and Mitsubishi. 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 GOE290 typically compare it against profiles of similar thickness: NASA LRN 1015 (NASA TM 102840), GOE 741 AIRFOIL, NASA/LANGLEY LS(1)-0421MOD AIRFOIL, NACA M8 AIRFOIL, SARATOV AIRFOIL. The EH 2.0/7.0 is another reference profile frequently considered alongside it.
Aircraft Using the GOE290 Airfoil
Junkers G38 | Junkers | Goettingen 290 ? | Goettingen 565 ? |
Mitsubishi Ki-20 | Mitsubishi | Goettingen 290 ? | Goettingen 565 ? |
Wing lofting: 2 of these aircraft taper from GOE290 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 GOE290 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.5%) and max camber (6.2%).