Airfoil Data
M8
NACA M8 AIRFOIL
Wing Geometry Simulator
The NACA M8 AIRFOIL is a 12.5% chord-thickness airfoil with a maximum camber of 6.3% at 25% 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 -6.3°.
Thin airfoil theory predicts a stall angle near 11.4° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the M8 typically compare it against profiles of similar thickness: NASA/LANGLEY LS(1)-0421MOD AIRFOIL, SARATOV AIRFOIL, GOE 510 AIRFOIL, EPPLER 694 AIRFOIL, GOE 741 AIRFOIL. The NACA M14 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the M8 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.5%) and max camber (6.3%).
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