Airfoil Data
HS1620
HAM-STD HS1-620 AIRFOIL
Wing Geometry Simulator
The HAM-STD HS1-620 AIRFOIL is a 14.0% chord-thickness airfoil with a maximum camber of 7.0% at 38% 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 -7.0°.
Thin airfoil theory predicts a stall angle near 10.9° and a peak lift-to-drag ratio around 71 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 HS1620 typically compare it against profiles of similar thickness: Eiffel 385 (S.T. Ae), CHEN AIRFOIL, FX 76-MP-140, GOE 227 (MVA H.37) AIRFOIL, Dayton-Wright 6. The DSMA-523B AIRFOIL is another reference profile frequently considered alongside it.
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AeroSheet loads HS1620 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Install in Google Sheets coming soonRelated Airfoils
Engineers evaluating the HS1620 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (14.0%) and max camber (7.0%).
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