Airfoil Data
CH10SM

The CH10 (smoothed) is a thick 16.2% chord-thickness airfoil with a maximum camber of 8.1% at 42% 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 -8.1°.

Thin airfoil theory predicts a stall angle near 10.1° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the CH10SM typically compare it against profiles of similar thickness: GOE 511 AIRFOIL, IST-MT1-18, Rhode St. Genese 36, DRAGONFLY CANARD, FX 72-LS-160. The ONERA HOR07 AIRFOIL is another reference profile frequently considered alongside it.