Airfoil Data
UA79SF18
UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL
Wing Geometry Simulator
The UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL is a 13.0% chord-thickness airfoil with a maximum camber of 6.5% at 47% 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 -6.5°.
Thin airfoil theory predicts a stall angle near 11.3° 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 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the UA79SF18 typically compare it against profiles of similar thickness: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT, EPPLER 1211 AIRFOIL, WORTMANN FX 2 AIRFOIL, GOE 675 AIRFOIL, GOE 646 AIRFOIL. The GOE 428 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the UA79SF18 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.0%) and max camber (6.5%).
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