Airfoil Data
GOE257

The GOE 257 AIRFOIL is a 8.5% chord-thickness airfoil with a maximum camber of 4.2% 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 -4.2°.

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 GOE257 typically compare it against profiles of similar thickness: AS6095 | Ananda-Selig | AIAA Paper 2018-0310, S1046 17% (Danny Howell), EPPLER 335 AIRFOIL, AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/], NASA/LANGLEY LS(1)-0413MOD AIRFOIL. The EPPLER 68 AIRFOIL is another reference profile frequently considered alongside it.