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 =     0.070 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2158   0.03134   0.02152  -0.0254   1.0000   0.1441
  -1.000  -0.1137   0.02764   0.01702  -0.0237   1.0000   0.1474
   0.000  -0.0152   0.02558   0.01505  -0.0220   1.0000   0.1726
   1.000   0.0826   0.02268   0.01487  -0.0197   1.0000   1.0000
   2.000   0.2191   0.02578   0.01725  -0.0281   0.9775   1.0000
   3.000   0.4270   0.02729   0.01878  -0.0463   0.9016   1.0000
   4.000   0.6376   0.02259   0.01466  -0.0555   0.8063   1.0000
   5.000   0.7804   0.02012   0.01016  -0.0489   0.3885   1.0000
   6.000   0.8842   0.02587   0.01448  -0.0471   0.2438   1.0000
   7.000   0.9888   0.03143   0.02023  -0.0455   0.1978   1.0000
   8.000   1.0752   0.03779   0.02719  -0.0414   0.1661   1.0000
   9.000   1.1377   0.04563   0.03593  -0.0344   0.1154   1.0000
  10.000   1.1827   0.05564   0.04663  -0.0266   0.1179   1.0000