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 =     0.020 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2284   0.04019   0.02583  -0.0258   1.0000   0.3527
  -1.000  -0.1116   0.03469   0.02006  -0.0261   1.0000   0.4304
   0.000  -0.0014   0.03090   0.01681  -0.0210   1.0000   1.0000
   1.000   0.0802   0.03238   0.01665  -0.0173   1.0000   1.0000
   2.000   0.1584   0.03449   0.01810  -0.0149   1.0000   1.0000
   3.000   0.2330   0.03741   0.02088  -0.0133   1.0000   1.0000
   4.000   0.3000   0.04161   0.02533  -0.0129   1.0000   1.0000
   5.000   0.3466   0.04869   0.03304  -0.0150   1.0000   1.0000
   6.000   0.6119   0.06512   0.05115  -0.0553   0.7222   1.0000
   7.000   0.7752   0.06910   0.05596  -0.0508   0.5241   1.0000
   8.000   0.7501   0.08881   0.07558  -0.0511   0.4885   1.0000
   9.000   0.7293   0.10961   0.09631  -0.0562   0.4948   1.0000
  10.000   0.5766   0.12965   0.11603  -0.0678