Airfoil Data
E545

The EPPLER 545 AIRFOIL is a 10.5% chord-thickness airfoil with a maximum camber of 5.2% at 40% 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 -5.2°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 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 E545 typically compare it against profiles of similar thickness: GOE 529 AIRFOIL, NACA 747A415, NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL, NACA 16-021, NACA 66-021 AIRFOIL. The EH 2.0/7.0 is another reference profile frequently considered alongside it.