Airfoil Data
RAF69

The RAF 69 AIRFOIL is a 11.9% chord-thickness airfoil with a maximum camber of 5.9% 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 -5.9°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the RAF69 typically compare it against profiles of similar thickness: EPPLER 1200 AIRFOIL, FX 66-S-161 AIRFOIL, NACA 2-H-15 AIRFOIL, GOE 14 AIRFOIL, EPPLER 266 AIRFOIL. The GOE 775 AIRFOIL is another reference profile frequently considered alongside it.