Install Xfoil Windows
XFLR5 is a powerful Xfoil application for foil analysis and 3D analysis for designing airplanes at low Reynolds numbers and their components individually. This free download is a standalone installer of XFLR Latest Version for Windows 32-bit and 64-bit. Stripped down version of XFOIL as compiled python module. If you are on a Windows machine (64bit) with Python 3.6, installing XFoil is a simple matter of.
I am trying to write a code in MATLAB that would be able to call up XFOIL from the MATLAB shell and have it run simulations. The closest I can get to doing so is writing a Perl wrapper to take inputs, generate a config file for XFOIL to use, then have XFOIL load it.
The issue is, I plan on many many iterations of this, and there's no 'scripting language' within XFOIL to write an XFOIL script. I don't want to have to manually type in 'oper; iter 100; alfa _____' for as many iterations as I need. The idea was something like this:
while (answer unconverged)
use initial guess/previous iteration to generate config file for XFOIL
open XFOIL, load config file
have XFOIL automatically generate CL, CD, other data
return values back to MATLAB
end
Is there any way to get XFOIL to run these commands with having to manually type them in?
Thanks for the help!
General
This is a stripped down version of XFOIL, presented in the form of a Python module. What's unique about this packagew.r.t. many others out there allowing an interface to XFOIL, is the fact that the Python code talks directly to acompiled Fortran library. This approach avoids having to read/write in-/output files to the disk and communicating withthe XFOIl executable. Eliminating the need for constant disk I/O operations can significantly speed up parallelframeworks in particular, giving this approach a clear advantage.
Building and Installing the Python Module
If you are on a Windows machine (64bit) with Python 3.6, installing XFoil is a simple matter of running:
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If you are using a different type of machine, or a different version of Python, you will have to make sure somesoftware is installed on your system in order for the package to be successfully built. First of all, the module targetsPython 3, and does NOT support Python 2. So make sure a Python 3 environment is installed and available.Furthermore, working compilers for C and Fortran have to be installed and on the PATH. On Windows, the build andinstallation have ONLY been tested with MinGW, using gcc and gfortran.
Then, installing XFoil should be as simple as running
from the root of the downloaded repository.
On Windows, you may have to force the system to use MinGW. To do so, create a file named distutils.cfg inPYTHONPATHLibdistutils with the following contents:
If you are not able to create this file for your Python environment, you can instead create a file named setup.cfg inthe root of the repo with the same contents. It is also possible to force the use of MinGW directly when invokingpip by calling:
Using the Module
All XFoil operations are performed using the XFoil class. So the first step when using this module is to create aninstance of this class:
If this does not produce any errors, the installation should be functioning properly.
The symmetric NACA 0012 airfoil is included as a test case. It can be loaded into the XFoil library like this:
Once the airfoil has been loaded successfully it can be analyzed. Let's analyze it for a range of angles of attack, at aReynolds number of one million. Let's limit the maximum number of iterations to 40 (the default is 20) as well.For the range of angles of attack, we will go from -20 degrees to 20 degrees with steps of 0.5 degrees:
The XFOIL library should produce a lot of output, which should be familiar to those who have used the original XFOILapplication before. The final result are lists of angles of attack, a, and the corresponding lift coefficients, cl,drag coefficients, cd, moment coefficients, cm, and minimum pressure coefficients cp. We can now, for example, plot the lift curve for this airfoil:
This should produce the following figure:
Just like in the original XFOIL application, an airfoil can also analyzed for a single angle of attack, single liftcoefficient, or a range of lift coefficients. The commands for these operations are
to analyze for an angle of attack of 10 degrees, a lift coefficient of 1.0, and for a range of lift coefficients from-0.5 to 0.5 with steps of 0.05.
For other features and specifics, see the documentation in the Python source files.