Airfoil Data
FX61147

The FX 61-147 AIRFOIL is a 10.6% chord-thickness airfoil with a maximum camber of 5.3% at 34% 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 -5.3°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The FX61147 appears in the wing design of at least 2 documented aircraft, including designs from Lanzalone and Monnett. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the FX61147 typically compare it against profiles of similar thickness: GOE 775 AIRFOIL, USA 27 AIRFOIL, NACA 23018, NACA 5-H-15 AIRFOIL, EPPLER 342 AIRFOIL. The HQ 2.5/9.0 smoothed by Eppler is another reference profile frequently considered alongside it.