Airfoil Data
N5H20
NACA 5-H-20 AIRFOIL
Wing Geometry Simulator
The NACA 5-H-20 AIRFOIL is a 14.4% chord-thickness airfoil with a maximum camber of 7.2% 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 -7.2°.
Thin airfoil theory predicts a stall angle near 10.8° and a peak lift-to-drag ratio around 72 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the N5H20 typically compare it against profiles of similar thickness: GOE 223 (MVA H.34) AIRFOIL, GOE 735 AIRFOIL, NACA M27 AIRFOIL, WORTMANN FX 08-S-176 AIRFOIL, Eiffel 371 (Monge). The M6 (65%) is another reference profile frequently considered alongside it.
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Engineers evaluating the N5H20 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (14.4%) and max camber (7.2%).
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