Airfoil Data
GOE741

The GOE 741 AIRFOIL is a 12.5% chord-thickness airfoil with a maximum camber of 6.2% at 30% 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.

Designers evaluating the GOE741 typically compare it against profiles of similar thickness: NASA LRN 1015 (NASA TM 102840), GOE 290 (MVA 290) AIRFOIL, NASA/LANGLEY LS(1)-0421MOD AIRFOIL, NACA M8 AIRFOIL, SARATOV AIRFOIL. The LOCKHEED C-141 BL610.61 AIRFOIL is another reference profile frequently considered alongside it.