XFOIL         Version 6.94
  
 Calculated polar for: woubair4                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.026 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.5234   0.04527   0.03131  -0.0619  0.4387  1.0012
   0.250   0.5601   0.04798   0.03421  -0.0641  0.4270  1.0012
   0.500   0.5901   0.05070   0.03717  -0.0652  0.4097  1.0012
   0.750   0.6191   0.05234   0.03907  -0.0658  0.4007  1.0012
   1.000   0.6481   0.05426   0.04122  -0.0665  0.3934  1.0012
   1.250   0.6750   0.05639   0.04351  -0.0667  0.3819  1.0012
   1.500   0.7021   0.05847   0.04580  -0.0671  0.3754  1.0012
   1.750   0.7292   0.06116   0.04868  -0.0678  0.3728  1.0012
   2.000   0.7537   0.06348   0.05126  -0.0681  0.3676  1.0012
   2.250   0.7771   0.06654   0.05443  -0.0682  0.3620  1.0012
   2.500   0.7986   0.06953   0.05784  -0.0689  0.3671  1.0012
   2.750   0.8195   0.07324   0.06188  -0.0700  0.3786  1.0012
   3.000   0.8832   0.07260   0.06183  -0.0794  0.4589  1.0012
   3.250   0.8982   0.07529   0.06492  -0.0816  0.4742  1.0012
   3.500   0.9081   0.07930   0.06916  -0.0832  0.4867  1.0012
   3.750   0.8895   0.08403   0.07416  -0.0835  0.5026  1.0012
   4.000   0.8598   0.08990   0.08012  -0.0828  0.5183  1.0012
   4.250   0.8217   0.09626   0.08647  -0.0816  0.5346  1.0012
   4.500   0.7844   0.10327   0.09341  -0.0816  0.5533  1.0012
   4.750   0.7567   0.10961   0.09968  -0.0825  0.5735  1.0012
   5.000   0.7350   0.11536   0.10536  -0.0837  0.5951  1.0012