XFOIL         Version 6.8
  
 Calculated polar for: RG-15 8.9%                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =    .000     Re =      .150 e 6     Ncrit =   9.000
  
   alpha     CL        CD       CDp       CM    Top Xtr Bot Xtr
  ------- -------- --------- --------- -------- ------- -------
  -2.000   -.1313    .01126    .00604   -.0290  1.0000   .8045
  -1.500   -.0815    .01141    .00620   -.0268   .9956   .8917
  -1.000    .0004    .01182    .00646   -.0314   .9750   .9804
   1.000    .3618    .01086    .00495   -.0604   .8968  1.0000
   1.500    .4296    .01050    .00458   -.0620   .8651  1.0000
   2.000    .4889    .01034    .00435   -.0618   .8258  1.0000
   2.500    .5429    .01037    .00433   -.0606   .7796  1.0000
   3.000    .5947    .01056    .00438   -.0589   .7283  1.0000
   3.500    .6442    .01089    .00458   -.0570   .6707  1.0000
   4.000    .6924    .01135    .00491   -.0550   .6086  1.0000
   4.500    .7389    .01192    .00532   -.0528   .5399  1.0000
   5.000    .7840    .01267    .00590   -.0505   .4674  1.0000
   5.500    .8276    .01357    .00659   -.0482   .3858  1.0000
   6.000    .8692    .01475    .00749   -.0458   .2936  1.0000
   6.500    .9082    .01642    .00881   -.0434   .1989  1.0000
   7.000    .9444    .01865    .01068   -.0406   .1240  1.0000
   7.500    .9801    .02099    .01286   -.0378   .0778  1.0000
   8.000   1.0081    .02441    .01618   -.0340   .0452  1.0000