Airfoil Data
NLF416

The NASA NLF(1)-0416 is a 10.4% chord-thickness airfoil with a maximum camber of 5.2% at 30% 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 NLF416 typically compare it against profiles of similar thickness: AH 88-K-130/20, GOE 500 AIRFOIL, I.S.A. 960, DAVIS BASIC B-24 WING AIRFOIL, GOE 238 (HANSA-BRANDENBURG) AIRFOIL. The GOE 704 AIRFOIL is another reference profile frequently considered alongside it.