Airfoil Data
NPL9510

The NPL 9510 AIRFOIL is a thin 4.9% chord-thickness airfoil with a maximum camber of 2.5% at 48% 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 -2.5°.

Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 49 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 NPL9510 typically compare it against profiles of similar thickness: HAM-STD HS1-404 AIRFOIL, JX-GS-04, NPL AIRFOIL FROM ARC CP 1372, RG 14A-1.4/7.0 AIRFOIL, NACA 1408. The LA2573A is another reference profile frequently considered alongside it.