Airfoil Data
FX05188

The WORTMANN FX 05-188 AIRFOIL is a 11.9% chord-thickness airfoil with a maximum camber of 6.0% at 43% 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 FX05188 appears in the wing design of at least 4 documented aircraft, including designs from Issoire and PIK-16a. 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 FX05188 typically compare it against profiles of similar thickness: GOE 233 (MVA CA4) AIRFOIL, NASA NLF(1)-1015, GOE 627 AIRFOIL, GOE 364 AIRFOIL, USA 33 AIRFOIL. The GOE 416A AIRFOIL is another reference profile frequently considered alongside it.