Package xfoil-697-1001

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 Set environment variable OSMAP to "/sw/share/xfoil/osmap.dat" if it is desired to use the option to see individual-frequency plotting on the A/Ao plot.c This package compiles xfoil with double precision arithmetic.