Airfoil Data
AS6095

The AS6095 | Ananda-Selig | AIAA Paper 2018-0310 is a 8.5% chord-thickness airfoil with a maximum camber of 4.2% at 39% 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 -4.2°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 AS6095 typically compare it against profiles of similar thickness: S1046 17% (Danny Howell), GOE 257 AIRFOIL, EPPLER 335 AIRFOIL, AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/], NASA/LANGLEY LS(1)-0413MOD AIRFOIL. The MH 42 8.94% is another reference profile frequently considered alongside it.