Airfoil Data
LA2573A

The LA2573A is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 26% 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 -5.0°.

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 LA2573A typically compare it against profiles of similar thickness: GOE 7K AIRFOIL, GOE 574 AIRFOIL, EPPLER 598 AIRFOIL, MARSKE XM-1D AIRFOIL (F14-3.0), NACA 63(3)-218. The GOE 564 AIRFOIL is another reference profile frequently considered alongside it.