Airfoil Data
NLR1T

The NLR-1T AIRFOIL is a thin 5.6% chord-thickness airfoil with a maximum camber of 2.8% at 34% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -2.8°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 51 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 NLR1T typically compare it against profiles of similar thickness: RAF 15 AIRFOIL, NACA 65-209, AG54, NACA 64-209, SIKORSKY SSC-A09 AIRFOIL. The Falcon is another reference profile frequently considered alongside it.