Airfoil Data
GU255118

The UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL is a thick 17.1% chord-thickness airfoil with a maximum camber of 8.5% at 45% 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 -8.5°.

Thin airfoil theory predicts a stall angle near 9.8° and a peak lift-to-drag ratio around 75 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 17% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GU255118 typically compare it against profiles of similar thickness: GOE 421 AIRFOIL, N-24, GOE 525 AIRFOIL, GOE 523 AIRFOIL, GOE 440 AIRFOIL. The SIKORSKY SSC-A07 AIRFOIL is another reference profile frequently considered alongside it.