XFOIL         Version 6.94
  
 Calculated polar for: BOIS RENAN G. 3                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.030 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.6306   0.05942   0.04821   0.0628  0.9998  0.3126
  -2.750  -0.6160   0.05825   0.04667   0.0641  0.9998  0.3180
  -2.500  -0.5990   0.05730   0.04533   0.0650  0.9998  0.3213
  -2.250  -0.5739   0.05577   0.04391   0.0640  0.9998  0.3372
  -2.000  -0.5451   0.05512   0.04279   0.0623  0.9998  0.3477
  -1.750  -0.5019   0.05435   0.04193   0.0572  0.9998  0.3715
  -1.500  -0.4553   0.05393   0.04140   0.0513  0.9998  0.4017
  -1.250  -0.4049   0.05383   0.04120   0.0445  0.9998  0.4431
  -1.000  -0.3374   0.05387   0.04162   0.0341  0.9998  0.5068
  -0.750  -0.2508   0.05453   0.04320   0.0197  0.9998  0.6141
  -0.500  -0.0403   0.06274   0.05143  -0.0190  0.9998  1.0002
  -0.250  -0.0235   0.06434   0.05267  -0.0193  0.9998  1.0002
   0.000  -0.0076   0.06599   0.05402  -0.0194  0.9998  1.0002
   0.250   0.0083   0.06761   0.05540  -0.0193  0.9998  1.0002
   0.500   0.0231   0.06935   0.05693  -0.0194  0.9998  1.0002
   0.750   0.0387   0.07103   0.05848  -0.0194  0.9998  1.0002
   1.000   0.0533   0.07284   0.06011  -0.0195  0.9998  1.0002
   1.250   0.0684   0.07465   0.06179  -0.0195  0.9998  1.0002
   1.500   0.0827   0.07648   0.06350  -0.0198  0.9998  1.0002
   1.750   0.0977   0.07837   0.06529  -0.0198  0.9998  1.0002
   2.000   0.1127   0.08033   0.06715  -0.0200  0.9998  1.0002
   2.250   0.1271   0.08230   0.06905  -0.0202  0.9998  1.0002
   2.500   0.1413   0.08440   0.07108  -0.0205  0.9998  1.0002
   2.750   0.1558   0.08647   0.07307  -0.0208  0.9998  1.0002