XFLR5: Download, Setup and Airfoil Analysis
A practical starting point for airfoil and wing analysis, with official downloads and a first experiment you can document.
Last reviewed: September 29, 2026sourceforge.net ↗Quick answers before you download
Is XFLR5 free?
Yes. XFLR5 is free software distributed under the GNU General Public License. It provides XFOIL-based airfoil analysis and additional wing and aircraft analysis methods. See the developer's project page for its scope and limitations.
Where is the official download?
Use the XFLR5 file archive on SourceForge, linked by the developer. Choose a release and inspect its files for your operating system; an automatically selected download can be a Windows package.
Is XFLR5 still being developed?
The developer says XFLR5 development ended on June 30, 2026, with no further releases or code updates planned. The same page identifies flow5 as its successor, released as open source on January 1, 2026. Keep XFLR5 when a course or existing project requires it; evaluate the successor for a new workflow.
Does XFLR5 work on Mac or Linux?
The project has supported Windows, macOS and Linux, but binary availability and compatibility vary by release. Check the archive and build instructions before assuming that a download supports your current OS or processor.
Windows, macOS and Linux setup
| Platform | Where to start | Check before running |
|---|---|---|
| Windows | The official archive lists a 64-bit Windows ZIP for version 6.62. | Extract the whole archive and retain its accompanying libraries. Read the release notes. |
| macOS | Inspect the release folders for a Mac build and its instructions. | Check macOS version and processor compatibility. The availability of older Mac builds does not establish native Apple Silicon support. |
| Linux | Check your distribution's package repository or use the project's compilation instructions with the source release. | Package versions can differ. Match the Qt/build dependencies to the source you are compiling. |
Record the version and OS in your project notes so someone else can reproduce your results. If your course supplies a known working environment, start there. This guide does not certify every archived binary on current operating systems.
XFLR5 vs. XFOIL vs. OpenVSP
| Tool | Main purpose | Useful starting task |
|---|---|---|
| XFOIL | Design and analysis of isolated subsonic airfoils. | Study a two-dimensional airfoil and its lift/drag polars. |
| XFLR5 | XFOIL airfoil capabilities plus lifting-line, vortex-lattice and panel methods for wings and model aircraft. | Compare airfoils and explore a wing's lift distribution and stability. |
| OpenVSP | Parametric aircraft geometry, with aerodynamic analysis through VSPAERO. | Explore whole-aircraft geometry and configuration tradeoffs. |
These methods make different assumptions. A more detailed-looking model is not automatically more accurate. Read the XFLR5 limitations documentation and NASA's VSPAERO introduction before interpreting results near stall or outside a solver's intended range.
Your first airfoil comparison
- Ask a small question. For example: how does camber change the predicted lift curve at a fixed Reynolds number?
- Choose two airfoils. Start with a symmetric NACA 0012 and a cambered NACA 4412. Use identical analysis settings for both.
- Set and record your assumptions. Include Reynolds number, transition settings, angle-of-attack range and software version.
- Run a modest angle sweep. Inspect convergence. Do not quietly turn missing or unconverged points into valid measurements.
- Export two plots. Compare lift coefficient against angle of attack and the drag polar. Explain one difference and one limitation.
Deliverable: a one-page comparison with the input settings, plots and a justified airfoil choice for a stated task. Simulated results are predictions, not flight-test measurements.
Next, explore the OpenVSP guide, choose a hands-on aerospace project, or connect this work to the aerospace engineering pathway.