XFOIL         Version 6.94
  
 Calculated polar for: FX 77-W-121                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3135   0.01405   0.00497  -0.0327  0.4666  0.0653
   0.500   0.3626   0.01459   0.00575  -0.0315  0.4813  0.0775
   1.000   0.4089   0.01416   0.00604  -0.0296  0.4790  0.3193
   1.500   0.4603   0.01509   0.00588  -0.0285  0.4768  0.0516
   2.000   0.5080   0.01533   0.00581  -0.0265  0.4644  0.0319
   2.500   0.5558   0.01400   0.00483  -0.0245  0.4479  0.0960
   3.000   0.8606   0.01141   0.00388  -0.0778  0.3962  1.0000
   3.500   0.8594   0.01177   0.00427  -0.0657  0.4073  0.9900
   4.000   0.9098   0.01282   0.00560  -0.0652  0.4216  0.9906
   5.500   1.0816   0.01220   0.00480  -0.0663  0.3614  1.0000
   6.000   1.1302   0.01442   0.00797  -0.0659  0.4170  1.0000
   6.500   1.1707   0.01494   0.00856  -0.0637  0.4127  1.0000
   7.000   0.9732   0.01401   0.00491  -0.0070  0.3560  0.0560
   7.500   1.1246   0.01917   0.01022  -0.0372  0.0493  1.0000
   8.000   1.2988   0.01422   0.00814  -0.0556  0.3734  1.0000
   9.000   1.2445   0.01968   0.01197  -0.0296  0.1229  1.0000
  10.000   1.1604   0.03130   0.02309  -0.0149  0.0226  1.0000
  10.500   1.1480   0.03710   0.02914  -0.0151  0.0175  1.0000
  11.000   1.1459   0.04255   0.03498  -0.0134  0.0178  1.0000
  11.500   1.1264   0.04961   0.04243  -0.0126  0.0084  1.0000
  12.000   1.1041   0.05718   0.05000  -0.0127  0.0064  1.0000