Airfoil Data
HS1620

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.