Airfoil Data
AS6096
AS6096 | Ananda-Selig | AIAA Paper 2018-0310
Wing Geometry Simulator
The AS6096 | Ananda-Selig | AIAA Paper 2018-0310 is a 8.9% chord-thickness airfoil with a maximum camber of 4.5% at 34% 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 -4.5°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 AS6096 typically compare it against profiles of similar thickness: LOCKHEED L-188 ROOT AIRFOIL, APEX 16, GOE 117 (MVA MK.4) AIRFOIL, GOE 79 (PFALZ 11) AIRFOIL, NACA 2414. The FX 66-S-196 V1 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the AS6096 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.9%) and max camber (4.5%).
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