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 =     0.090 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2158   0.03019   0.02075  -0.0240   1.0000   0.1208
  -1.000  -0.1166   0.02628   0.01638  -0.0227   1.0000   0.1250
   0.000  -0.0187   0.02460   0.01473  -0.0215   1.0000   0.1429
   1.000   0.1193   0.02188   0.01494  -0.0269   0.9875   1.0000
   2.000   0.3379   0.02315   0.01558  -0.0469   0.9195   1.0000
   3.000   0.5123   0.02223   0.01480  -0.0563   0.8673   1.0000
   4.000   0.6949   0.01660   0.00952  -0.0591   0.7571   1.0000
   5.000   0.7881   0.01873   0.00906  -0.0506   0.3260   1.0000
   6.000   0.8788   0.02341   0.01272  -0.0468   0.2143   1.0000
   7.000   0.9849   0.02822   0.01734  -0.0458   0.1747   1.0000
   8.000   1.0780   0.03273   0.02211  -0.0429   0.1454   1.0000
   9.000   1.1582   0.03819   0.02801  -0.0382   0.1183   1.0000
  10.000   1.2134   0.04576   0.03658  -0.0303   0.0972   1.0000