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 =     0.035 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2188   0.03558   0.02359  -0.0273   1.0000   0.2289
  -1.000  -0.1085   0.03153   0.01854  -0.0261   1.0000   0.2492
   0.000  -0.0017   0.02826   0.01593  -0.0248   1.0000   0.3548
   1.000   0.0810   0.02708   0.01547  -0.0180   1.0000   1.0000
   2.000   0.1616   0.02938   0.01717  -0.0161   1.0000   1.0000
   3.000   0.2376   0.03253   0.02020  -0.0152   1.0000   1.0000
   4.000   0.3040   0.03709   0.02500  -0.0154   1.0000   1.0000
   5.000   0.7404   0.03029   0.02004  -0.0527   0.6740   1.0000
   6.000   0.8817   0.03333   0.02094  -0.0462   0.3784   1.0000
   7.000   0.9849   0.04241   0.03025  -0.0442   0.3021   1.0000
   8.000   1.0361   0.05422   0.04325  -0.0373   0.2684   1.0000
   9.000   1.0105   0.07129   0.06151  -0.0279   1.0000   0.2289
  10.000   0.8809   0.10142   0.09194  -0.0312