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 =     0.040 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.1760   0.04797   0.03469  -0.0424  0.4172  0.3182
  -2.500   0.2370   0.04869   0.03485  -0.0428  0.3723  0.3313
  -2.000   0.3335   0.04850   0.03435  -0.0505  0.3438  0.3526
  -1.500   0.4837   0.04846   0.03430  -0.0702  0.3284  0.3873
  -1.000   0.6099   0.04964   0.03580  -0.0857  0.3147  0.4358
  -0.500   0.7076   0.05253   0.03911  -0.0952  0.3079  0.4950
   0.000   0.7670   0.05458   0.04206  -0.0958  0.3030  0.5567
   0.500   0.8294   0.05756   0.04564  -0.0974  0.2988  0.5880
   1.000   0.8863   0.06121   0.04994  -0.0981  0.2943  0.6144
   1.500   0.9361   0.06559   0.05522  -0.0975  0.2922  0.6545
   2.000   0.9704   0.07021   0.06139  -0.0934  0.3022  1.0024
   2.500   1.0108   0.07834   0.07006  -0.0939  0.3299  1.0024