XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL958.89 AIRFOIL
                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2162   0.03079   0.02125  -0.0247   1.0000   0.1325
  -1.000  -0.1155   0.02724   0.01688  -0.0229   1.0000   0.1346
   0.000  -0.0168   0.02504   0.01486  -0.0218   1.0000   0.1558
   1.000   0.0827   0.02205   0.01490  -0.0202   1.0000   1.0000
   2.000   0.2969   0.02470   0.01668  -0.0409   0.9408   1.0000
   3.000   0.4785   0.02464   0.01673  -0.0527   0.8819   1.0000
   4.000   0.6786   0.01864   0.01121  -0.0582   0.7816   1.0000
   5.000   0.7848   0.01940   0.00953  -0.0499   0.3526   1.0000
   6.000   0.8822   0.02463   0.01353  -0.0471   0.2275   1.0000
   7.000   0.9862   0.02964   0.01870  -0.0455   0.1848   1.0000
   8.000   1.0760   0.03509   0.02459  -0.0420   0.1544   1.0000
   9.000   1.1475   0.04160   0.03180  -0.0360   0.1268   1.0000
  10.000   1.2030   0.05024   0.04106  -0.0291   0.1059   1.0000