Airfoil Data
AS5045
AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]
Wing Geometry Simulator
The AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/] is a 8.5% chord-thickness airfoil with a maximum camber of 4.2% at 37% 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 AS5045 typically compare it against profiles of similar thickness: NASA/LANGLEY LS(1)-0413MOD AIRFOIL, SD7032-099-88, EPPLER 335 AIRFOIL, GOE 257 AIRFOIL, AS6095 | Ananda-Selig | AIAA Paper 2018-0310. The MH 122 9.32% is another reference profile frequently considered alongside it.
Related Airfoils
Engineers evaluating the AS5045 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.5%) and max camber (4.2%).