Airfoil Data
N24

The N-24 is a thick 17.1% chord-thickness airfoil with a maximum camber of 8.6% at 30% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -8.6°.

Thin airfoil theory predicts a stall angle near 9.8° and a peak lift-to-drag ratio around 75 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 17% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the N24 typically compare it against profiles of similar thickness: GOE 421 AIRFOIL, UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL, GOE 525 AIRFOIL, GOE 523 AIRFOIL, GOE 440 AIRFOIL. The NACA 65(2)-415 a=0.5 is another reference profile frequently considered alongside it.