Airfoil Data
NLF414F

The NASA NLF(1)-0414F is a 9.5% chord-thickness airfoil with a maximum camber of 4.7% at 47% 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 -4.7°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 62 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 NLF414F typically compare it against profiles of similar thickness: P-51D ROOT (BL17.5) AIRFOIL, GOE 282 (DAIMLER XIII) AIRFOIL, EPPLER 403 AIRFOIL, GOE 395 AIRFOIL, Eiffel 428 (Bleriot). The IST-MT1-24 is another reference profile frequently considered alongside it.