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 =     0.060 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2150   0.03216   0.02187  -0.0261   1.0000   0.1580
  -1.000  -0.1124   0.02847   0.01736  -0.0244   1.0000   0.1651
   0.000  -0.0128   0.02632   0.01530  -0.0224   1.0000   0.1948
   1.000   0.0823   0.02348   0.01492  -0.0192   1.0000   1.0000
   2.000   0.1646   0.02600   0.01681  -0.0178   1.0000   1.0000
   3.000   0.3654   0.02968   0.02044  -0.0380   0.9347   1.0000
   4.000   0.5822   0.02796   0.01929  -0.0523   0.8363   1.0000
   5.000   0.7757   0.02099   0.01100  -0.0481   0.4394   1.0000
   6.000   0.8856   0.02730   0.01565  -0.0469   0.2656   1.0000
   7.000   0.9909   0.03367   0.02221  -0.0454   0.2152   1.0000
   8.000   1.0716   0.04118   0.03051  -0.0405   0.1824   1.0000
   9.000   1.1233   0.05072   0.04106  -0.0325   0.1548   1.0000
  10.000   1.1195   0.06451   0.05615  -0.0208   0.1393   1.0000