Airfoil Data
NLF0115

The NASA NLF(1)-0115 is a 9.3% chord-thickness airfoil with a maximum camber of 4.6% at 39% 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 -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 NLF0115 typically compare it against profiles of similar thickness: GOE 287 AIRFOIL, CAL2263m, US1000ROOT, GOE 436 AIRFOIL, BOEING VERTOL V43012-1.58 AIRFOIL. The GOE 492 AIRFOIL is another reference profile frequently considered alongside it.