Airfoil Data
FX61184

The FX 61-184 AIRFOIL is a 12.0% chord-thickness airfoil with a maximum camber of 6.0% at 37% 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 -6.0°.

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.

The FX61184 appears in the wing design of at least 59 documented aircraft, including designs from Nihon and TeST. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the FX61184 typically compare it against profiles of similar thickness: EPPLER 398 AIRFOIL, GOE 567 AIRFOIL, USA 33 AIRFOIL, EPPLER 1214 AIRFOIL, GOE 405 AIRFOIL. The EPPLER 554 AIRFOIL is another reference profile frequently considered alongside it.