XFOIL         Version 6.94
  
 Calculated polar for: wouaibair2                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.020 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.0012   0.06600   0.05134  -0.0115  0.9976  0.4743
  -2.500   0.0520   0.06648   0.05262  -0.0111  0.9976  0.4941
  -2.000   0.1125   0.06659   0.05391  -0.0117  0.9976  0.5167
  -1.500   0.2553   0.05855   0.04799  -0.0273  0.8302  0.5665
  -1.000   0.4308   0.05422   0.04194  -0.0436  0.5288  0.6551
  -0.500   0.5146   0.05463   0.04263  -0.0466  0.4908  0.7469
   0.000   0.5905   0.05428   0.04307  -0.0474  0.4742  0.8931
   0.500   0.7450   0.05814   0.04637  -0.0744  0.4523  1.0024
   1.000   0.8435   0.06311   0.05110  -0.0872  0.4456  1.0024
   1.500   0.9090   0.06868   0.05675  -0.0920  0.4384  1.0024
   2.000   0.9543   0.07526   0.06367  -0.0937  0.4395  1.0024
   2.500   0.9749   0.08312   0.07190  -0.0922  0.4429  1.0024
   3.000   0.9770   0.09261   0.08176  -0.0900  0.4555  1.0024
   3.500   0.9278   0.10537   0.09484  -0.0848  0.4802  1.0024
   4.000   0.7175   0.12849   0.11844  -0.0788  0.5611  1.0024
   4.500   0.6013   0.14524   0.13534  -0.0826  0.7131  1.0024