Airfoil Data
NLF415

The NASA/DLR NLF(2)-0415 is a 9.1% chord-thickness airfoil with a maximum camber of 4.6% at 54% 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 -4.6°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 NLF415 typically compare it against profiles of similar thickness: GOE 617 AIRFOIL, EPPLER 336 AIRFOIL, MH 94 16.03%, S4180-098-84, SG6051. The W1011 is another reference profile frequently considered alongside it.