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LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il)
Reynolds number: 50,000
Max Cl/Cd: 33.37 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141e-il-50000.txt
Download as CSV file: xf-c141e-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL761.11 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4457   0.11067   0.10293  -0.0191   1.0000   0.2785
  -9.000  -0.4728   0.11030   0.10272  -0.0190   1.0000   0.2898
  -8.750  -0.4583   0.10650   0.09893  -0.0172   1.0000   0.3060
  -8.500  -0.4452   0.10286   0.09531  -0.0156   1.0000   0.3213
  -8.250  -0.4389   0.09978   0.09228  -0.0140   1.0000   0.3366
  -8.000  -0.4380   0.09721   0.08977  -0.0121   1.0000   0.3543
  -7.750  -0.4471   0.09543   0.08810  -0.0097   1.0000   0.3742
  -7.500  -0.4648   0.09419   0.08699  -0.0065   1.0000   0.3928
  -7.250  -0.4383   0.09055   0.08332  -0.0039   1.0000   0.4255
  -7.000  -0.4141   0.08694   0.07970  -0.0017   1.0000   0.4553
  -6.750  -0.4049   0.08426   0.07707   0.0010   1.0000   0.4846
  -6.500  -0.3921   0.08166   0.07449   0.0039   1.0000   0.5191
  -6.250  -0.3856   0.07984   0.07271   0.0078   1.0000   0.5610
  -6.000  -0.3597   0.07640   0.06926   0.0094   1.0000   0.6016
  -5.000  -0.5243   0.04689   0.03811  -0.0222   1.0000   0.1816
  -4.750  -0.5052   0.04350   0.03371  -0.0219   1.0000   0.1709
  -4.500  -0.4854   0.04075   0.03062  -0.0211   1.0000   0.1705
  -4.250  -0.4638   0.03818   0.02770  -0.0204   1.0000   0.1699
  -4.000  -0.4408   0.03601   0.02509  -0.0197   1.0000   0.1704
  -3.750  -0.4180   0.03385   0.02285  -0.0191   1.0000   0.1749
  -3.500  -0.3936   0.03219   0.02097  -0.0185   1.0000   0.1794
  -3.250  -0.3678   0.03080   0.01919  -0.0180   1.0000   0.1855
  -3.000  -0.3424   0.02934   0.01766  -0.0175   1.0000   0.1939
  -2.750  -0.3163   0.02832   0.01637  -0.0169   1.0000   0.2042
  -2.500  -0.2904   0.02715   0.01527  -0.0164   1.0000   0.2180
  -2.250  -0.2638   0.02619   0.01433  -0.0158   1.0000   0.2362
  -2.000  -0.2372   0.02524   0.01351  -0.0154   1.0000   0.2605
  -1.750  -0.2118   0.02423   0.01278  -0.0149   1.0000   0.3002
  -1.500  -0.1483   0.02131   0.01265  -0.0168   1.0000   1.0000
  -1.250  -0.1332   0.02138   0.01230  -0.0149   1.0000   1.0000
  -1.000  -0.1173   0.02149   0.01211  -0.0133   1.0000   1.0000
  -0.750  -0.1005   0.02165   0.01201  -0.0119   1.0000   1.0000
  -0.500  -0.0828   0.02185   0.01200  -0.0108   1.0000   1.0000
  -0.250  -0.0645   0.02210   0.01206  -0.0097   1.0000   1.0000
   0.000  -0.0458   0.02238   0.01218  -0.0088   1.0000   1.0000
   0.250  -0.0268   0.02270   0.01236  -0.0080   1.0000   1.0000
   0.500  -0.0075   0.02307   0.01261  -0.0073   1.0000   1.0000
   0.750   0.0119   0.02347   0.01291  -0.0066   1.0000   1.0000
   1.000   0.0313   0.02391   0.01327  -0.0061   1.0000   1.0000
   1.250   0.0508   0.02440   0.01368  -0.0055   1.0000   1.0000
   1.500   0.0702   0.02492   0.01416  -0.0051   1.0000   1.0000
   1.750   0.0895   0.02549   0.01469  -0.0047   1.0000   1.0000
   2.000   0.1086   0.02611   0.01529  -0.0043   1.0000   1.0000
   2.250   0.1276   0.02677   0.01595  -0.0040   1.0000   1.0000
   2.500   0.1463   0.02749   0.01667  -0.0038   1.0000   1.0000
   2.750   0.1648   0.02827   0.01747  -0.0036   1.0000   1.0000
   3.000   0.1828   0.02911   0.01835  -0.0035   1.0000   1.0000
   3.250   0.2005   0.03002   0.01931  -0.0034   1.0000   1.0000
   3.500   0.2541   0.03174   0.02115  -0.0101   0.9847   1.0000
   3.750   0.3275   0.03322   0.02284  -0.0198   0.9497   1.0000
   4.000   0.3895   0.03409   0.02393  -0.0264   0.9190   1.0000
   4.250   0.4506   0.03437   0.02449  -0.0320   0.8871   1.0000
   4.500   0.5255   0.03343   0.02390  -0.0378   0.8489   1.0000
   4.750   0.6065   0.03020   0.02114  -0.0411   0.7982   1.0000
   5.000   0.6783   0.02607   0.01751  -0.0412   0.7418   1.0000
   5.250   0.7392   0.02215   0.01329  -0.0374   0.5663   1.0000
   5.500   0.7547   0.02408   0.01347  -0.0328   0.3910   1.0000
   5.750   0.7790   0.02635   0.01500  -0.0318   0.3128   1.0000
   6.000   0.8096   0.02833   0.01661  -0.0319   0.2664   1.0000
   6.250   0.8390   0.03021   0.01828  -0.0319   0.2348   1.0000
   6.500   0.8667   0.03208   0.02004  -0.0317   0.2114   1.0000
   6.750   0.8934   0.03409   0.02200  -0.0313   0.1937   1.0000
   7.000   0.9166   0.03614   0.02425  -0.0303   0.1805   1.0000
   7.250   0.9389   0.03852   0.02685  -0.0292   0.1710   1.0000
   7.500   0.9616   0.04070   0.02909  -0.0284   0.1621   1.0000
   7.750   0.9785   0.04358   0.03236  -0.0266   0.1576   1.0000
   8.000   0.9908   0.04641   0.03569  -0.0242   0.1537   1.0000
   8.250   1.0044   0.04912   0.03867  -0.0223   0.1494   1.0000
   8.500   1.0256   0.05238   0.04182  -0.0219   0.1452   1.0000
   8.750   1.0312   0.05596   0.04587  -0.0192   0.1448   1.0000
   9.000   1.0341   0.05983   0.05016  -0.0165   0.1447   1.0000
   9.250   1.0337   0.06388   0.05458  -0.0139   0.1448   1.0000
   9.500   1.0311   0.06813   0.05914  -0.0114   0.1450   1.0000
   9.750   0.9657   0.07430   0.06618  -0.0053   0.1534   1.0000
  10.000   0.9427   0.07934   0.07138  -0.0031   0.1562   1.0000
  10.250   0.9289   0.08444   0.07655  -0.0019   0.1585   1.0000
  10.500   0.9298   0.08969   0.08187  -0.0017   0.1608   1.0000
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