Airfoil Data
FX61147
FX 61-147 AIRFOIL
Wing Geometry Simulator
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.
Aircraft Using the FX61147 Airfoil
Lanzalone Aulanz | Lanzalone | Wortmann FX 61-147 | Constant |
Monnett Moni | Monnett | Wortmann FX 61-147 | Constant |
Design wings in your spreadsheet
AeroSheet loads FX61147 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Install in Google Sheets coming soonRelated Airfoils
Engineers evaluating the FX61147 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.6%) and max camber (5.3%).
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