Airfoil Data
S1046

The S1046 17% (Danny Howell) is a 8.5% chord-thickness airfoil with a maximum camber of 4.2% at 31% 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 S1046 typically compare it against profiles of similar thickness: AS6095 | Ananda-Selig | AIAA Paper 2018-0310, 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 GOE 275 (DAIMLER VI) AIRFOIL is another reference profile frequently considered alongside it.