Airfoil Data
N5H15

The NACA 5-H-15 AIRFOIL is a 10.6% chord-thickness airfoil with a maximum camber of 5.3% at 40% 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 -5.3°.

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 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the N5H15 typically compare it against profiles of similar thickness: NACA 23018, EPPLER 342 AIRFOIL, GOE 775 AIRFOIL, USA 27 AIRFOIL, EPPLER 544 AIRFOIL. The NACA 2-H-15 AIRFOIL is another reference profile frequently considered alongside it.