Airfoil Data
FX61163
FX 61-163 AIRFOIL
Wing Geometry Simulator
The FX 61-163 AIRFOIL is a 10.7% chord-thickness airfoil with a maximum camber of 5.4% 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 -5.4°.
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 FX61163 appears in the wing design of at least 48 documented aircraft, including designs from Industria and Ruschmeyer. 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 FX61163 typically compare it against profiles of similar thickness: FX 60-160 AIRFOIL, GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL, NASA/LANGLEY LS(1)-0417MOD AIRFOIL, GOE 633 AIRFOIL, USA 40 AIRFOIL. The GOE 5K AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the FX61163 Airfoil
Wing lofting: 39 of these aircraft taper from FX61163 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 FX61163 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.7%) and max camber (5.4%).