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 =     0.040 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2167   0.03469   0.02308  -0.0272   1.0000   0.2068
  -1.000  -0.1104   0.03072   0.01824  -0.0256   1.0000   0.2234
   0.000  -0.0048   0.02808   0.01580  -0.0240   1.0000   0.2913
   1.000   0.0813   0.02606   0.01529  -0.0182   1.0000   1.0000
   2.000   0.1624   0.02842   0.01704  -0.0165   1.0000   1.0000
   3.000   0.2385   0.03162   0.02013  -0.0157   1.0000   1.0000
   4.000   0.4018   0.03753   0.02644  -0.0327   0.9455   1.0000
   5.000   0.7617   0.02578   0.01587  -0.0503   0.6147   1.0000
   6.000   0.8838   0.03163   0.01937  -0.0461   0.3438   1.0000
   7.000   0.9883   0.04015   0.02816  -0.0444   0.2763   1.0000
   8.000   1.0540   0.05077   0.03975  -0.0383   0.2419   1.0000
   9.000   1.0565   0.06520   0.05552  -0.0281   0.2217   1.0000
  10.000   0.9434   0.08837   0.07952  -0.0211   0.2303   1.0000