Airfoil Data
OA213

The ONERA OA213 AIRFOIL is a 9.6% chord-thickness airfoil with a maximum camber of 4.8% 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 -4.8°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 62 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the OA213 typically compare it against profiles of similar thickness: EPPLER 407 AIRFOIL, FX 60-126/1 AIRFOIL, RAF 6 AIRFOIL, GOE 167 (V.KARMAN PROP.2) AIRFOIL, EPPLER STE 871-514 AIRFOIL. The GOE 511 AIRFOIL is another reference profile frequently considered alongside it.