Airfoil Data
MB253515SM

The MB253515 15.0% smoothed is a 9.9% chord-thickness airfoil with a maximum camber of 5.0% at 35% 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 63 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 MB253515SM typically compare it against profiles of similar thickness: DORNIER A-5 AIRFOIL, GOE 593 AIRFOIL, LISSAMAN 7769 AIRFOIL, GOE 746 AIRFOIL, EPPLER 341 AIRFOIL. The GOE 393 AIRFOIL is another reference profile frequently considered alongside it.