Principal Investigator Mark Drela
Project Website http://web.mit.edu/drela/Public/web/xfoil/
XFOIL is an interactive program for the design and analysis of subsonic isolated airfoils.
It consists of a collection of menu-driven routines which perform various useful functions such as:
(*) 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
(*) 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
(*) 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)
(*) Blending of airfoils(*) Writing and reading of airfoil coordinates and polar save files(*) Plotting of geometry, pressure distributions, and multiple polars