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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2181   0.02921   0.02034  -0.0238   
  -1.000  -0.1184   0.02588   0.01625  -0.0221   1.0000   0.1167
   0.000  -0.0002   0.02445   0.01474  -0.0247   0.9949   0.1353
   1.000   0.1773   0.02145   0.01465  -0.0369   0.9637   1.0000
   2.000   0.3714   0.02160   0.01442  -0.0515   0.9055   1.0000
   3.000   0.5399   0.01995   0.01293  -0.0590   0.8544   1.0000
   4.000   0.7144   0.01498   0.00813  -0.0611   0.7274   1.0000
   5.000   0.7902   0.01817   0.00865  -0.0512   0.3068   1.0000
   6.000   0.8774   0.02253   0.01211  -0.0468   0.2039   1.0000
   7.000   0.9800   0.02665   0.01618  -0.0451   0.1662   1.0000
   8.000   1.0733   0.03080   0.02057  -0.0422   0.1382   1.0000
   9.000   1.1543   0.03572   0.02591  -0.0376   
  10.000   1.2146   0.04310   0.03409  -0.0306   0.0909   1.0000