Airfoil Data
GOE648
GOE 648 AIRFOIL
Wing Geometry Simulator
The GOE 648 AIRFOIL is a 11.5% chord-thickness airfoil with a maximum camber of 5.7% at 29% 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 -5.7°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 68 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 GOE648 typically compare it against profiles of similar thickness: GOE 533 AIRFOIL, GOE 553 AIRFOIL, EPPLER STE 87(-3)-914 AIRFOIL, AH 81-K-144/17, UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL. The Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE648 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.5%) and max camber (5.7%).
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