Airfoil Data
LA203A

The DOUGLAS LA203A AIRFOIL is a 13.2% chord-thickness airfoil with a maximum camber of 6.6% at 40% 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 -6.6°.

Thin airfoil theory predicts a stall angle near 11.2° 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 LA203A typically compare it against profiles of similar thickness: GOE 624 AIRFOIL, WORTMANN FX 057-816, WORTMANN FX 049-915 AIRFOIL, AH 93-W-257, GOE 535 AIRFOIL. The GOE 510 AIRFOIL is another reference profile frequently considered alongside it.