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 =     0.030 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2212   0.03683   0.02416  -0.0272   
  -1.000  -0.1070   0.03248   0.01889  -0.0266   1.0000   0.2854
   0.000  -0.0100   0.02661   0.01633  -0.0216   1.0000   1.0000
   1.000   0.0807   0.02836   0.01573  -0.0177   1.0000   1.0000
   2.000   0.1607   0.03061   0.01737  -0.0157   1.0000   1.0000
   3.000   0.2364   0.03369   0.02033  -0.0146   1.0000   1.0000
   4.000   0.3031   0.03815   0.02502  -0.0147   1.0000   1.0000
   5.000   0.6303   0.04276   0.03134  -0.0529   0.7601   1.0000
   6.000   0.8806   0.03575   0.02312  -0.0473   0.4244   1.0000
   7.000   0.9745   0.04551   0.03325  -0.0440   0.3382   1.0000
   8.000   1.0076   0.05911   0.04800  -0.0370   0.3058   1.0000
   9.000   0.9690   0.07858   0.06824  -0.0305   0.2977   1.0000
  10.000   0.9167   0.10484   0.09464  -0.0326