Airfoil Data
OAF095

The OAF095 AIRFOIL is a thin 7.8% chord-thickness airfoil with a maximum camber of 3.9% at 38% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.9°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 57 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 OAF095 typically compare it against profiles of similar thickness: GOE 374 AIRFOIL, AG37, GOE 114 (MVA MK.1) AIRFOIL, GOE 595 AIRFOIL, MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID). The E230 (9.96%) is another reference profile frequently considered alongside it.