Airfoil Data
N6H20

The NACA 6-H-20 AIRFOIL is a thick 16.1% chord-thickness airfoil with a maximum camber of 8.1% at 40% 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 -8.1°.

Thin airfoil theory predicts a stall angle near 10.2° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the N6H20 typically compare it against profiles of similar thickness: GOE 798 AIRFOIL, GOE 625 AIRFOIL, UA(2)-180 (University of Alberta/Marsden), UA(2)-180 smoothed, original ycoord oscillate +-0.0003, EPPLER 862 STRUT AIRFOIL. The NACA 63-210 AIRFOIL is another reference profile frequently considered alongside it.