airgeobookcode_m/dump.out at master · sobester/airgeobookcode_m · GitHub

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 ===================================================
  XFOIL Version 6.97
  Copyright (C) 2000   Mark Drela, Harold Youngren

  This software comes with ABSOLUTELY NO WARRANTY,
    subject to the GNU General Public License.

  Caveat computor
 ===================================================

 File  xfoil.def  not found

   QUIT    Exit program

  .OPER    Direct operating point(s)
  .MDES    Complex mapping design routine
  .QDES    Surface speed design routine
  .GDES    Geometry design routine

   SAVE f  Write airfoil to labeled coordinate file
   PSAV f  Write airfoil to plain coordinate file
   ISAV f  Write airfoil to ISES coordinate file
   MSAV f  Write airfoil to MSES coordinate file
   REVE    Reverse written-airfoil node ordering
   DELI i  Change written-airfoil file delimiters

   LOAD f  Read buffer airfoil from coordinate file
   NACA i  Set NACA 4,5-digit airfoil and buffer airfoil
   INTE    Set buffer airfoil by interpolating two airfoils
   NORM    Buffer airfoil normalization toggle
   HALF    Halve the number of points in buffer airfoil
   XYCM rr Change CM reference location, currently  0.25000 0.00000

   BEND    Display structural properties of current airfoil

   PCOP    Set current-airfoil panel nodes directly from buffer airfoil points
   PANE    Set current-airfoil panel nodes ( 160 ) based on curvature
  .PPAR    Show/change paneling

  .PLOP    Plotting options

   WDEF f  Write  current-settings file
   RDEF f  Reread current-settings file
   NAME s  Specify new airfoil name
   NINC    Increment name version number

   Z       Zoom    | (available in all menus)
   U       Unzoom  |

 XFOIL   c>
 Plain airfoil file

Enter airfoil name   s>
 Number of input coordinate points: 201
 Clockwise ordering
 Max thickness =     0.200074  at x =   0.295
 Max camber    =     0.034965  at x =   0.454

  LE  x,y  =  -0.00082   0.00862  |   Chord =   1.00086
  TE  x,y  =   1.00000   0.00000  |

 Current airfoil nodes set from buffer airfoil nodes ( 201 )

 XFOIL   c>
 Blunt trailing edge.  Gap =  0.00416

 Paneling parameters used...
   Number of panel nodes       160
   Panel bunching parameter    1.000
   TE/LE panel density ratio   0.150
   Refined-area/LE panel density ratio    0.200
   Top    side refined area x/c limits  1.000 1.000
   Bottom side refined area x/c limits  1.000 1.000

 XFOIL   c>   ...............................................

  G raphics-enable flag:        T
  S ize of plot object          10.00"
  A spect ratio of plot object   0.5500
  P age dimensions              11.00 x  8.50"
  M argins from page edges       0.00",  0.00"
  F ont size (relative)          0.0150
  W indow/screen size fraction   0.8000
  B lowup input method:        Cursor
  O rientation of plot:        Landscape
  C olor PostScript output?     F

      Option, Value   (or <Return>)    c>   ...............................................

  G raphics-enable flag:        F
  S ize of plot object          10.00"
  A spect ratio of plot object   0.5500
  P age dimensions              11.00 x  8.50"
  M argins from page edges       0.00",  0.00"
  F ont size (relative)          0.0150
  W indow/screen size fraction   0.8000
  B lowup input method:        Cursor
  O rientation of plot:        Landscape
  C olor PostScript output?     F

      Option, Value   (or <Return>)    c>
 XFOIL   c>
.OPERi   c>
 M  =    0.0000
 Re =  0.2142E+06

.OPERv   c>
 Sonic Cp =   -498.93      Sonic Q/Qinf =    24.856


.OPERv   c>
 M  =    0.0367
 Re =  0.2142E+06

.OPERv   c>
 Polar  1 newly created for accumulation
 Airfoil archived with polar: GuyMartin

Enter  polar save filename  OR  <return> for no file   s>
              Current                         Save file
          ------------------              ------------------
 name :   GuyMartin                                       GuyMartin
 Re   :        214213.                         214000.
 Mach :         0.0367                          0.0370
 Retyp:         1                               1
 Matyp:         1                               1
 Ncrit:         9.0000                          9.0000
 xtr T:         1.0000                          1.0000
 xtr B:         1.0000                          1.0000

 Current parameters different from old save file values.

Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>
Set current parameters to old save file values ? y/n>