Airfoil Data
GOE29B
GOE 29B AIRFOIL
Wing Geometry Simulator
The GOE 29B AIRFOIL is a 11.2% chord-thickness airfoil with a maximum camber of 5.6% at 30% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.6°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE29B typically compare it against profiles of similar thickness: FX 63-145 AIRFOIL, FX 84-W-140, NACA 66(3)-418, EPPLER STF 863-615 AIRFOIL, DAI 1238. The RAE 5214 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE29B frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.2%) and max camber (5.6%).
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