Airfoil Data
NACA4421
NACA 4421
Wing Geometry Simulator
The NACA 4421 is a 14.3% chord-thickness airfoil with a maximum camber of 7.1% 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 -7.1°.
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 NACA4421 typically compare it against profiles of similar thickness: GOE 604 AIRFOIL, Glenn Martin 2, GOE 620 AIRFOIL, NACA M27 AIRFOIL, FX 73-170 A. The NACA 4412 is another reference profile frequently considered alongside it.
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Engineers evaluating the NACA4421 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (14.3%) and max camber (7.1%).
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