XFOIL is an interactive program for the design and analysis of subsonic isolated airfoils. Subsonic Airfoil Development System. It consists of a collection of menu-driven routines which perform various useful functions such as:
1. Viscous (or inviscid) analysis of an existing airfoil, allowing:
* forced or free transition
* transitional separation bubbles
* limited trailing edge separation
* lift and drag predictions just beyond CLmax
* Karman-Tsien compressibility correction
* fixed or varying Reynolds and/or Mach numbers
2. Airfoil design and redesign by interactive modification of surface speed distributions, in two methods:
* Full-Inverse method, based on a complex-mapping formulation
* Mixed-Inverse method, an extension of XFOIL's basic panel method
3. Airfoil redesign by interactive modification of geometric parameters such as:
* max thickness and camber, highpoint position
* LE radius, TE thickness
* camber line via geometry specification
* camber line via loading change specification
* flap deflection
* explicit contour geometry (via screen cursor)
4. Blending of airfoils
5. Writing and reading of airfoil coordinates and polar save files
6. Plotting of geometry, pressure distributions, and multiple polars

XFOIL is best suited for use on a good workstation. A high-end PC is also effective, but must run Unix to support the X-Windows graphics. The source code of XFOIL is Fortran 77. The plot library also uses a few C routines for the X-Windows interface.

XFOIL has been tested on the following systems:
1. DEC-5000
2. Alpha
3. SGI
4. *Sun
5. *RS/6000
6. *HP-9000
7. *Pentium/Linux

The systems marked with "*" have peculiar features which require slight modifications to the Makefiles in the plotlib/ and bin/ directories. Examine these Makefiles before building the plot library and XFOIL.

The license of this software is Free, you can free download and free use this calculator software.