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.
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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%).
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