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 =     0.015 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2504   0.04321   0.02832  -0.0189   1.0000   0.4552
  -1.000  -0.1435   0.03634   0.02232  -0.0167   1.0000   0.6127
   0.000   0.0011   0.03452   0.01765  -0.0210   1.0000   1.0000
   1.000   0.0802   0.03589   0.01751  -0.0173   1.0000   1.0000
   2.000   0.1572   0.03791   0.01884  -0.0145   1.0000   1.0000
   3.000   0.2307   0.04074   0.02150  -0.0126   1.0000   1.0000
   4.000   0.2974   0.04476   0.02580  -0.0118   1.0000   1.0000
   5.000   0.3478   0.05118   0.03287  -0.0131   1.0000   1.0000
   6.000   0.3659   0.06265   0.04503  -0.0190   1.0000   1.0000
   7.000   0.5238   0.08494   0.06842  -0.0520   0.8278   1.0000
   8.000   0.6059   0.10077   0.08476  -0.0596   0.7008   1.0000
   9.000   0.6018   0.11637   0.10044  -0.0626   0.7202   1.0000
  10.000   0.4706   0.11779   0.10142  -0.0451   1.0000   1.0000