XFOIL         Version 6.94
  
 Calculated polar for: FX 80-080                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3337   0.00679   0.00260  -0.0812  0.8642  0.8896
   0.500   0.3836   0.00676   0.00258  -0.0796  0.8515  0.9066
   1.000   0.4352   0.00672   0.00253  -0.0785  0.8375  0.9204
   1.500   0.4865   0.00662   0.00244  -0.0771  0.8194  0.9345
   2.000   0.5415   0.00653   0.00238  -0.0766  0.8012  0.9508
   2.500   0.6039   0.00641   0.00229  -0.0778  0.7701  0.9689
   3.000   0.6753   0.00641   0.00234  -0.0812  0.7342  0.9886
   3.500   0.7240   0.00659   0.00245  -0.0799  0.6764  1.0000
   4.000   0.7443   0.00813   0.00289  -0.0727  0.4329  1.0000
   4.500   0.7704   0.01027   0.00385  -0.0678  0.1866  1.0000
   5.000   0.8095   0.01170   0.00476  -0.0652  0.0814  1.0000
   5.500   0.8512   0.01300   0.00587  -0.0628  0.0392  1.0000
   6.000   0.8921   0.01446   0.00743  -0.0600  0.0283  1.0000
   6.500   0.9319   0.01605   0.00914  -0.0573  0.0215  1.0000
   7.000   0.9714   0.01789   0.01110  -0.0546  0.0148  1.0000
   7.500   1.0131   0.01962   0.01301  -0.0522  0.0103  1.0000
   8.000   1.0503   0.02370   0.01755  -0.0491  0.0086  1.0000
   8.500   1.0883   0.02659   0.02086  -0.0464  0.0072  1.0000
   9.000   1.1159   0.03114   0.02600  -0.0424  0.0067  1.0000
   9.500   1.1278   0.03664   0.03212  -0.0368  0.0064  1.0000
  10.000   1.0644   0.05180   0.04859  -0.0230  0.0076  1.0000
  10.500   1.0152   0.06113   0.05839  -0.0166  0.0078  1.0000
  11.000   0.9696   0.07153   0.06911  -0.0170  0.0081  1.0000
  11.500   0.9262   0.08609   0.08393  -0.0251  0.0082  1.0000
  12.000   0.8886   0.11077   0.10863  -0.0417  0.0087  1.0000