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 =     0.080 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.3125   0.03761   0.02439  -0.0708  0.2430  0.1615
  -2.500   0.4318   0.03685   0.02314  -0.0847  0.2351  0.1702
  -2.000   0.5148   0.03814   0.02472  -0.0915  0.2278  0.2688
  -1.500   0.5914   0.04040   0.02707  -0.0964  0.2249  0.2932
  -1.000   0.6589   0.04275   0.02968  -0.0992  0.2227  0.3191
  -0.500   0.7227   0.04530   0.03267  -0.1014  0.2185  0.3485
   0.000   0.7824   0.04791   0.03584  -0.1028  0.2119  0.3880
   0.500   0.8405   0.05078   0.03889  -0.1042  0.2037  0.4259
   1.000   0.8961   0.05684   0.04534  -0.1056  0.1982  0.4490