Airfoil Data
USA26

The USA 26 AIRFOIL is a 9.1% chord-thickness airfoil with a maximum camber of 4.6% 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 -4.6°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 USA26 typically compare it against profiles of similar thickness: BOEING-VERTOL VR-7 AIRFOIL WITH TAB, BOEING-VERTOL VR-7 AIRFOIL, USA 45 M AIRFOIL, CLARK V AIRFOIL, FX 83-W-108. The NACA 4412 is another reference profile frequently considered alongside it.