Airfoil Data
GOE321

The GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL is a 10.7% chord-thickness airfoil with a maximum camber of 5.4% 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 -5.4°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 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 GOE321 typically compare it against profiles of similar thickness: FX 60-160 AIRFOIL, GOE 633 AIRFOIL, FX 61-163 AIRFOIL, USA 40 AIRFOIL, NASA/LANGLEY LS(1)-0417MOD AIRFOIL. The NASA SC(2)-0610 AIRFOIL is another reference profile frequently considered alongside it.