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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2156   0.03340   0.02253  -0.0266   
  -1.000  -0.1111   0.02935   0.01767  -0.0251   1.0000   0.1876
   0.000  -0.0091   0.02719   0.01555  -0.0230   1.0000   0.2299
   1.000   0.0819   0.02456   0.01504  -0.0187   1.0000   1.0000
   2.000   0.1636   0.02700   0.01688  -0.0172   1.0000   1.0000
   3.000   0.2569   0.03060   0.02038  -0.0198   0.9931   1.0000
   4.000   0.5096   0.03318   0.02351  -0.0459   0.8729   1.0000
   5.000   0.7738   0.02236   0.01240  -0.0485   0.5103   1.0000
   6.000   0.8873   0.02923   0.01721  -0.0468   0.2966   1.0000
   7.000   0.9910   0.03651   0.02480  -0.0450   0.2395   1.0000
   8.000   1.0665   0.04543   0.03456  -0.0396   0.2061   1.0000
   9.000   1.1089   0.05625   0.04644  -0.0311   0.1780   1.0000
  10.000   1.0586   0.07379   0.06542  -0.0184   0.1705   1.0000