Airfoil Data
FX75141
FX 75-141
Wing Geometry Simulator
The FX 75-141 is a 10.2% chord-thickness airfoil with a maximum camber of 5.1% at 40% 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 -5.1°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The FX75141 appears in the wing design of at least 1 documented aircraft — notably by Aceair. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the FX75141 typically compare it against profiles of similar thickness: FX 63-143 AIRFOIL, NACA M20 AIRFOIL, GOE 164 (MVA MK.10) AIRFOIL, EPPLER 542 AIRFOIL, GOE 575 AIRFOIL. The GOE 492 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the FX75141 Airfoil
Aceair Aeris 200 | Aceair | Wortmann FX 75-141 | NASA NLF(1)-0215F |
Wing lofting: 1 of these aircraft taper from FX75141 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the FX75141 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.2%) and max camber (5.1%).