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EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 407 AIRFOIL (e407-il)
Reynolds number: 100,000
Max Cl/Cd: 50.61 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e407-il-100000.txt
Download as CSV file: xf-e407-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 407 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4393   0.11619   0.11222  -0.0344   1.0000   0.1280
  -9.500  -0.4867   0.11447   0.11008  -0.0333   1.0000   0.1242
  -9.250  -0.5606   0.10923   0.10506  -0.0409   1.0000   0.1282
  -8.500  -0.4617   0.09771   0.09390  -0.0308   1.0000   0.1446
  -8.250  -0.4593   0.09464   0.09085  -0.0290   1.0000   0.1470
  -8.000  -0.4705   0.09059   0.08685  -0.0287   1.0000   0.1489
  -7.750  -0.4895   0.08588   0.08220  -0.0290   1.0000   0.1506
  -7.500  -0.5249   0.08090   0.07731  -0.0297   1.0000   0.1598
  -7.250  -0.5446   0.07668   0.07314  -0.0289   1.0000   0.1612
  -7.000  -0.5729   0.07290   0.06943  -0.0274   1.0000   0.1635
  -6.750  -0.6883   0.04912   0.04227  -0.0486   1.0000   0.0472
  -6.500  -0.6711   0.04425   0.03714  -0.0492   1.0000   0.0459
  -6.250  -0.6495   0.04053   0.03297  -0.0496   1.0000   0.0452
  -6.000  -0.6259   0.03755   0.02956  -0.0498   1.0000   0.0451
  -5.750  -0.6018   0.03535   0.02696  -0.0496   1.0000   0.0460
  -5.500  -0.5788   0.03301   0.02444  -0.0495   1.0000   0.0503
  -5.250  -0.5560   0.03154   0.02288  -0.0489   1.0000   0.0543
  -5.000  -0.5326   0.03019   0.02132  -0.0480   1.0000   0.0585
  -4.750  -0.5096   0.02876   0.02000  -0.0476   1.0000   0.0690
  -4.500  -0.4845   0.02753   0.01882  -0.0475   1.0000   0.0858
  -4.250  -0.4549   0.02601   0.01768  -0.0491   1.0000   0.1252
  -4.000  -0.4114   0.02362   0.01801  -0.0541   1.0000   0.5361
  -3.750  -0.3965   0.02491   0.01916  -0.0507   1.0000   0.5906
  -3.500  -0.3857   0.02622   0.02036  -0.0463   1.0000   0.6189
  -3.250  -0.3799   0.02748   0.02161  -0.0405   1.0000   0.6378
  -3.000  -0.3716   0.02854   0.02261  -0.0356   1.0000   0.6560
  -2.750  -0.3597   0.02939   0.02336  -0.0318   1.0000   0.6746
  -2.500  -0.3486   0.03011   0.02398  -0.0281   1.0000   0.6906
  -2.250  -0.3381   0.03069   0.02449  -0.0243   1.0000   0.7050
  -2.000  -0.3283   0.03116   0.02491  -0.0204   1.0000   0.7181
  -1.750  -0.3192   0.03152   0.02519  -0.0165   1.0000   0.7302
  -1.500  -0.3079   0.03180   0.02540  -0.0134   1.0000   0.7424
  -1.250  -0.2949   0.03202   0.02555  -0.0109   1.0000   0.7545
  -1.000  -0.2798   0.03222   0.02567  -0.0090   1.0000   0.7664
  -0.750  -0.2616   0.03244   0.02580  -0.0082   1.0000   0.7780
  -0.500  -0.2294   0.03342   0.02664  -0.0097   0.9941   0.7884
  -0.250  -0.1449   0.03507   0.02804  -0.0201   0.9524   0.7960
   0.000  -0.1028   0.03539   0.02822  -0.0238   0.9396   0.8018
   0.250  -0.0569   0.03583   0.02854  -0.0284   0.9299   0.8066
   0.500  -0.0268   0.03582   0.02847  -0.0296   0.9193   0.8107
   0.750   0.0063   0.03590   0.02848  -0.0317   0.9088   0.8150
   1.000   0.0494   0.03622   0.02871  -0.0360   0.8999   0.8194
   1.250   0.0830   0.03630   0.02877  -0.0375   0.8914   0.8230
   1.500   0.1114   0.03634   0.02879  -0.0386   0.8810   0.8270
   1.750   0.1514   0.03655   0.02896  -0.0419   0.8725   0.8311
   2.000   0.1912   0.03667   0.02907  -0.0450   0.8640   0.8346
   2.250   0.2171   0.03666   0.02907  -0.0453   0.8534   0.8383
   2.500   0.2572   0.03673   0.02915  -0.0481   0.8459   0.8423
   2.750   0.2950   0.03676   0.02920  -0.0508   0.8365   0.8461
   3.000   0.3252   0.03673   0.02921  -0.0519   0.8257   0.8498
   3.250   0.3712   0.03646   0.02898  -0.0549   0.8204   0.8537
   3.500   0.3997   0.03638   0.02896  -0.0558   0.8086   0.8575
   3.750   0.4338   0.03633   0.02898  -0.0577   0.7976   0.8615
   4.000   0.4768   0.03574   0.02848  -0.0598   0.7915   0.8655
   4.250   0.5077   0.03542   0.02824  -0.0606   0.7804   0.8697
   4.500   0.5412   0.03513   0.02806  -0.0619   0.7688   0.8738
   4.750   0.5917   0.03408   0.02713  -0.0649   0.7638   0.8780
   5.000   0.6217   0.03349   0.02668  -0.0649   0.7520   0.8827
   5.250   0.6564   0.03282   0.02614  -0.0658   0.7400   0.8875
   5.500   0.7113   0.03105   0.02453  -0.0688   0.7357   0.8917
   5.750   0.7439   0.02997   0.02363  -0.0687   0.7237   0.8966
   6.000   0.7807   0.02875   0.02258  -0.0692   0.7118   0.9022
   6.500   0.8678   0.02509   0.01932  -0.0710   0.6885   0.9132
   6.750   0.9130   0.02342   0.01782  -0.0723   0.6701   0.9188
   7.000   0.9529   0.02198   0.01651  -0.0727   0.6448   0.9255
   7.250   0.9956   0.02088   0.01543  -0.0739   0.6084   0.9322
   7.500   1.0250   0.02046   0.01496  -0.0733   0.5637   0.9400
   7.750   1.0441   0.02063   0.01500  -0.0716   0.5151   0.9490
   8.000   1.0590   0.02108   0.01525  -0.0694   0.4648   0.9611
   8.250   1.0705   0.02175   0.01573  -0.0672   0.4131   0.9969
   8.500   1.0831   0.02301   0.01670  -0.0658   0.3597   1.0000
   8.750   1.0929   0.02447   0.01791  -0.0642   0.3078   1.0000
   9.000   1.1016   0.02616   0.01928  -0.0627   0.2599   1.0000
   9.250   1.1103   0.02801   0.02086  -0.0614   0.2151   1.0000
   9.500   1.1195   0.03002   0.02265  -0.0602   0.1765   1.0000
   9.750   1.1299   0.03215   0.02454  -0.0591   0.1443   1.0000
  10.000   1.1422   0.03435   0.02650  -0.0584   0.1194   1.0000
  10.250   1.1579   0.03640   0.02858  -0.0579   0.0994   1.0000
  10.500   1.1788   0.03859   0.03070  -0.0578   0.0850   1.0000
  10.750   1.2016   0.04080   0.03293  -0.0581   0.0734   1.0000
  11.000   1.2358   0.04348   0.03562  -0.0594   0.0643   1.0000
  11.250   1.2583   0.04575   0.03794  -0.0597   0.0574   1.0000
  11.500   1.2878   0.04932   0.04188  -0.0604   0.0520   1.0000
  11.750   1.3027   0.05214   0.04498  -0.0596   0.0482   1.0000
  12.000   1.3243   0.05670   0.04958  -0.0605   0.0437   1.0000
  12.250   1.3199   0.05980   0.05315  -0.0578   0.0427   1.0000
  12.500   1.3134   0.06367   0.05746  -0.0553   0.0420   1.0000
  12.750   1.3024   0.06780   0.06200  -0.0529   0.0414   1.0000
  13.000   1.2876   0.07213   0.06671  -0.0508   0.0410   1.0000
  13.250   1.2699   0.07678   0.07170  -0.0493   0.0406   1.0000
  13.500   1.2501   0.08181   0.07704  -0.0484   0.0405   1.0000
  13.750   1.2282   0.08731   0.08284  -0.0483   0.0405   1.0000
  14.000   1.2046   0.09337   0.08917  -0.0492   0.0407   1.0000
  14.250   1.1799   0.10005   0.09610  -0.0511   0.0411   1.0000
  14.500   1.1550   0.10738   0.10365  -0.0543   0.0416   1.0000
  14.750   1.1311   0.11537   0.11181  -0.0585   0.0423   1.0000
  15.000   1.1086   0.12400   0.12058  -0.0636   0.0430   1.0000
  15.250   1.0894   0.13297   0.12963  -0.0691   0.0436   1.0000
  15.500   0.7753   0.15590   0.15321  -0.0713   0.0684   1.0000
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