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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 50,000
Max Cl/Cd: 38.57 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel428-il-50000-n5.txt
Download as CSV file: xf-eiffel428-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 428 (Bleriot)                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3350   0.09813   0.09156  -0.0338   1.0000   0.1315
  -8.750  -0.3460   0.09675   0.09034  -0.0341   1.0000   0.1366
  -8.500  -0.3702   0.09644   0.09027  -0.0363   1.0000   0.1385
  -8.250  -0.3512   0.09158   0.08539  -0.0321   1.0000   0.1430
  -8.000  -0.3544   0.08945   0.08338  -0.0312   1.0000   0.1481
  -7.750  -0.3802   0.08932   0.08345  -0.0337   1.0000   0.1529
  -7.500  -0.3769   0.08597   0.08019  -0.0294   1.0000   0.1560
  -7.250  -0.3825   0.08436   0.07867  -0.0263   1.0000   0.1619
  -7.000  -0.3847   0.08201   0.07638  -0.0284   0.9959   0.1708
  -6.750  -0.3611   0.07809   0.07241  -0.0330   0.9856   0.1863
  -6.500  -0.3132   0.06477   0.05831  -0.0572   0.9691   0.0932
  -6.250  -0.2883   0.06067   0.05419  -0.0591   0.9612   0.0888
  -6.000  -0.2596   0.05583   0.04907  -0.0644   0.9510   0.0860
  -5.750  -0.2310   0.05172   0.04464  -0.0688   0.9411   0.0874
  -5.500  -0.1959   0.04709   0.03956  -0.0738   0.9340   0.0850
  -5.250  -0.1671   0.04298   0.03484  -0.0768   0.9239   0.0822
  -5.000  -0.1305   0.03938   0.03052  -0.0802   0.9176   0.0805
  -4.750  -0.1017   0.03700   0.02769  -0.0814   0.9085   0.0807
  -4.500  -0.0651   0.03503   0.02551  -0.0840   0.9032   0.0847
  -4.250  -0.0376   0.03339   0.02347  -0.0846   0.8936   0.0868
  -4.000   0.0000   0.03147   0.02108  -0.0866   0.8880   0.0870
  -3.750   0.0275   0.03016   0.01940  -0.0866   0.8783   0.0874
  -3.500   0.0646   0.02878   0.01766  -0.0881   0.8720   0.0882
  -3.250   0.0950   0.02774   0.01632  -0.0883   0.8612   0.0895
  -3.000   0.1279   0.02678   0.01508  -0.0888   0.8505   0.0914
  -2.750   0.1637   0.02576   0.01390  -0.0896   0.8400   0.0961
  -2.500   0.1977   0.02492   0.01291  -0.0902   0.8285   0.1022
  -2.250   0.2271   0.02431   0.01212  -0.0899   0.8160   0.1059
  -2.000   0.2560   0.02378   0.01145  -0.0896   0.8045   0.1097
  -1.750   0.2869   0.02319   0.01079  -0.0898   0.7953   0.1160
  -1.500   0.3141   0.02278   0.01036  -0.0894   0.7841   0.1265
  -1.250   0.3408   0.02226   0.01007  -0.0890   0.7722   0.1555
  -1.000   0.3920   0.01938   0.00960  -0.0930   0.7607   1.0000
  -0.750   0.4204   0.01941   0.00923  -0.0924   0.7502   1.0000
  -0.500   0.4442   0.01959   0.00917  -0.0914   0.7384   1.0000
  -0.250   0.4694   0.01980   0.00916  -0.0907   0.7295   1.0000
   0.000   0.4958   0.01999   0.00917  -0.0903   0.7217   1.0000
   0.250   0.5201   0.02026   0.00932  -0.0897   0.7133   1.0000
   0.500   0.5463   0.02048   0.00942  -0.0893   0.7060   1.0000
   0.750   0.5702   0.02078   0.00965  -0.0886   0.6979   1.0000
   1.000   0.5959   0.02104   0.00983  -0.0882   0.6908   1.0000
   1.250   0.6198   0.02136   0.01013  -0.0875   0.6829   1.0000
   1.500   0.6450   0.02161   0.01035  -0.0870   0.6753   1.0000
   1.750   0.6682   0.02195   0.01069  -0.0862   0.6667   1.0000
   2.000   0.6938   0.02217   0.01092  -0.0857   0.6589   1.0000
   2.250   0.7158   0.02255   0.01134  -0.0847   0.6498   1.0000
   2.500   0.7419   0.02276   0.01155  -0.0843   0.6426   1.0000
   2.750   0.7628   0.02321   0.01209  -0.0833   0.6336   1.0000
   3.000   0.7891   0.02341   0.01236  -0.0828   0.6268   1.0000
   3.250   0.8091   0.02383   0.01288  -0.0816   0.6161   1.0000
   3.500   0.8307   0.02391   0.01301  -0.0801   0.6011   1.0000
   3.750   0.8524   0.02384   0.01298  -0.0784   0.5826   1.0000
   4.000   0.8727   0.02390   0.01308  -0.0767   0.5642   1.0000
   4.250   0.8924   0.02414   0.01341  -0.0752   0.5476   1.0000
   4.500   0.9114   0.02439   0.01375  -0.0735   0.5288   1.0000
   4.750   0.9310   0.02462   0.01410  -0.0719   0.5097   1.0000
   5.000   0.9509   0.02491   0.01448  -0.0705   0.4924   1.0000
   5.250   0.9688   0.02524   0.01489  -0.0687   0.4690   1.0000
   5.500   0.9871   0.02559   0.01528  -0.0669   0.4452   1.0000
   5.750   1.0027   0.02606   0.01576  -0.0649   0.4112   1.0000
   6.000   1.0161   0.02670   0.01638  -0.0626   0.3575   1.0000
   6.250   1.0235   0.02767   0.01682  -0.0594   0.2743   1.0000
   6.500   1.0247   0.02928   0.01800  -0.0561   0.2332   1.0000
   6.750   1.0281   0.03077   0.01939  -0.0532   0.1995   1.0000
   7.000   1.0269   0.03266   0.02105  -0.0503   0.1459   1.0000
   7.250   1.0230   0.03490   0.02299  -0.0475   0.1313   1.0000
   7.500   1.0212   0.03715   0.02517  -0.0452   0.1203   1.0000
   7.750   1.0205   0.03945   0.02749  -0.0432   0.1088   1.0000
   8.000   1.0249   0.04142   0.02970  -0.0417   0.0979   1.0000
   8.250   1.0347   0.04300   0.03162  -0.0402   0.0833   1.0000
   8.500   1.0425   0.04475   0.03346  -0.0392   0.0726   1.0000
   8.750   1.0467   0.04688   0.03546  -0.0382   0.0674   1.0000
   9.000   1.0491   0.04927   0.03776  -0.0373   0.0643   1.0000
   9.250   1.0511   0.05175   0.04023  -0.0361   0.0622   1.0000
   9.500   1.0552   0.05407   0.04264  -0.0349   0.0598   1.0000
   9.750   1.0597   0.05640   0.04495  -0.0336   0.0569   1.0000
  10.000   1.0732   0.05805   0.04670  -0.0316   0.0537   1.0000
  10.250   1.1073   0.05854   0.04740  -0.0292   0.0507   1.0000
  10.500   1.1654   0.05985   0.04881  -0.0279   0.0454   1.0000
  10.750   1.1856   0.06255   0.05195  -0.0270   0.0438   1.0000
  11.000   1.1989   0.06570   0.05549  -0.0260   0.0428   1.0000
  11.250   1.2034   0.06912   0.05925  -0.0251   0.0416   1.0000
  11.500   1.2045   0.07269   0.06310  -0.0242   0.0404   1.0000
  12.000   1.2179   0.08141   0.07210  -0.0235   0.0378   1.0000
  12.250   1.2019   0.08538   0.07637  -0.0231   0.0377   1.0000
  12.500   1.1856   0.08974   0.08103  -0.0232   0.0376   1.0000
  12.750   1.1691   0.09451   0.08606  -0.0239   0.0376   1.0000
  13.000   1.1522   0.09963   0.09142  -0.0251   0.0376   1.0000
  13.250   1.1355   0.10511   0.09711  -0.0269   0.0377   1.0000
  13.500   1.1184   0.11097   0.10317  -0.0292   0.0378   1.0000
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