Airfoil Data
AS6097

The AS6097 | Ananda-Selig | AIAA Paper 2018-0310 is a 9.8% chord-thickness airfoil with a maximum camber of 4.9% at 41% 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 -4.9°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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 AS6097 typically compare it against profiles of similar thickness: NACA 4412, CLARK Z AIRFOIL, AH 79-K-135/20 B, BOEING 106 AIRFOIL, EPPLER 546 AIRFOIL. The GOE 54 AIRFOIL is another reference profile frequently considered alongside it.