Airfoil Data
ARAD13

The ARA-D 13% AIRFOIL is a 10.1% chord-thickness airfoil with a maximum camber of 5.0% at 30% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.0°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the ARAD13 typically compare it against profiles of similar thickness: NACA 65(3)-218, FX 84-W-127, Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program), MRC-16, GOE 550 AIRFOIL. The NACA 64(4)-221 is another reference profile frequently considered alongside it.