Airfoil Data
AS5048
AS5048 (18%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]
Wing Geometry Simulator
The AS5048 (18%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/] is a 10.1% chord-thickness airfoil with a maximum camber of 5.1% at 38% 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 -5.1°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the AS5048 typically compare it against profiles of similar thickness: Fage & Collins 3, AH 93-K-132/15, GOE 526 AIRFOIL, USA 48 AIRFOIL, FX 60-157 AIRFOIL. The AIRFOIL PROFILE12A 9.00% is another reference profile frequently considered alongside it.
Related Airfoils
Engineers evaluating the AS5048 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.1%) and max camber (5.1%).