Airfoil Data
E58

The EPPLER 58 AIRFOIL is a 8.9% chord-thickness airfoil with a maximum camber of 4.5% at 50% chord, suited to transonic and supercritical wing sections where aft-camber reduces wave drag. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 E58 typically compare it against profiles of similar thickness: ARA-D 10% AIRFOIL, E201 (11.88%), NACA 11-H-09 AIRFOIL, GOE 309 (MVA H.41) AIRFOIL, GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL. The NACA 63,3-418 is another reference profile frequently considered alongside it.