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 =     0.025 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2235   0.03830   0.02483  -0.0270   1.0000   0.2941
  -1.000  -0.1067   0.03355   0.01930  -0.0270   1.0000   0.3385
   0.000  -0.0047   0.02844   0.01641  -0.0213   1.0000   1.0000
   1.000   0.0803   0.03004   0.01610  -0.0175   1.0000   1.0000
   2.000   0.1596   0.03222   0.01765  -0.0153   1.0000   1.0000
   3.000   0.2349   0.03524   0.02053  -0.0140   1.0000   1.0000
   4.000   0.3019   0.03957   0.02512  -0.0139   1.0000   1.0000
   5.000   0.4411   0.05051   0.03705  -0.0351   0.9254   1.0000
   6.000   0.8633   0.04041   0.02788  -0.0498   0.4953   1.0000
   7.000   0.9431   0.05070   0.03837  -0.0443   0.3938   1.0000
   8.000   0.9361   0.06786   0.05635  -0.0384   0.3653   1.0000
   9.000   0.8111   0.09757   0.08601  -0.0440   
  10.000   0.8913   0.12730   0.11657  -0.0827