Airfoil Data
UA2-180
UA(2)-180 (University of Alberta/Marsden)
Wing Geometry Simulator
The UA(2)-180 (University of Alberta/Marsden) is a thick 16.0% chord-thickness airfoil with a maximum camber of 8.0% at 37% 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 -8.0°.
Thin airfoil theory predicts a stall angle near 10.2° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the UA2-180 typically compare it against profiles of similar thickness: UA(2)-180 smoothed, original ycoord oscillate +-0.0003, GOE 798 AIRFOIL, EPPLER 858 AIRFOIL, GOE 382 AIRFOIL, NACA 6-H-20 AIRFOIL. The AS6098 | Ananda-Selig | AIAA Paper 2018-0310 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the UA2-180 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (16.0%) and max camber (8.0%).
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