XFOIL         Version 6.8
  
 Calculated polar for: RG 15A-1,8-11,0                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =    .000     Re =      .300 e 6     Ncrit =   9.000
  
   alpha     CL        CD       CDp       CM    Top Xtr Bot Xtr
  ------- -------- --------- --------- -------- ------- -------
  -2.000    .0325    .00835    .00368   -.0595   .9119   .7216
  -1.500    .0925    .00819    .00352   -.0594   .8923   .7577
  -1.000    .1508    .00810    .00336   -.0591   .8697   .7881
   -.500    .2062    .00804    .00325   -.0580   .8445   .8131
    .000    .2572    .00803    .00320   -.0562   .8155   .8363
    .500    .3076    .00804    .00316   -.0544   .7851   .8590
   1.000    .3572    .00809    .00312   -.0523   .7545   .8821
   1.500    .4039    .00813    .00312   -.0497   .7201   .9070
   2.000    .4518    .00821    .00310   -.0475   .6852   .9330
   2.500    .5121    .00836    .00317   -.0480   .6450   .9569
   3.000    .5836    .00847    .00314   -.0515   .5999   .9883
   3.500    .6616    .00886    .00339   -.0565   .5483   .9992
   4.000    .7031    .00924    .00362   -.0543   .5011  1.0000
   4.500    .7449    .00974    .00392   -.0519   .4516  1.0000
   5.000    .7892    .01031    .00432   -.0499   .4030  1.0000
   5.500    .8336    .01098    .00477   -.0480   .3441  1.0000
   6.500    .9205    .01273    .00599   -.0442   .2224  1.0000
   7.000    .9618    .01385    .00678   -.0423   .1625  1.0000
   7.500   1.0034    .01498    .00768   -.0403   .1166  1.0000
   8.000   1.0445    .01610    .00867   -.0383   .0859  1.0000
   8.500   1.0845    .01725    .00977   -.0362   .0649  1.0000
   9.000   1.1216    .01854    .01098   -.0337   .0427  1.0000