Airfoil Data
GOE546

The GOE 546 AIRFOIL is a 8.5% chord-thickness airfoil with a maximum camber of 4.3% at 40% 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 -4.3°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the GOE546 typically compare it against profiles of similar thickness: GOE 280 (DAIMLER XI) AIRFOIL, GOE 281 (DAIMLER XII) AIRFOIL, NASA/LANGLEY LS(1)-0413MOD AIRFOIL, SD7032-099-88, AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]. The NACA M2 is another reference profile frequently considered alongside it.