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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 50,000
Max Cl/Cd: 26.97 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel10-il-50000-n5.txt
Download as CSV file: xf-eiffel10-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 10 (Wright) - 1903 Wright Flyer 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3916   0.11526   0.10764  -0.0112   1.0000   0.0508
  -8.500  -0.3861   0.11384   0.10629  -0.0132   1.0000   0.0514
  -8.250  -0.3787   0.11264   0.10516  -0.0165   1.0000   0.0518
  -8.000  -0.3686   0.10801   0.10058  -0.0161   1.0000   0.0526
  -7.750  -0.3586   0.10437   0.09699  -0.0163   1.0000   0.0539
  -7.500  -0.3483   0.10152   0.09420  -0.0176   1.0000   0.0554
  -7.250  -0.3371   0.09894   0.09169  -0.0196   1.0000   0.0570
  -7.000  -0.3244   0.09673   0.08953  -0.0226   1.0000   0.0588
  -6.750  -0.3072   0.09541   0.08826  -0.0282   1.0000   0.0600
  -6.500  -0.2917   0.09288   0.08581  -0.0317   1.0000   0.0607
  -6.250  -0.2854   0.08857   0.08160  -0.0293   1.0000   0.0622
  -6.000  -0.2740   0.08571   0.07882  -0.0300   1.0000   0.0643
  -5.750  -0.2600   0.08331   0.07647  -0.0321   1.0000   0.0669
  -5.500  -0.2355   0.08202   0.07520  -0.0386   1.0000   0.0698
  -5.250  -0.2169   0.07952   0.07276  -0.0420   1.0000   0.0710
  -5.000  -0.2136   0.07597   0.06934  -0.0392   1.0000   0.0728
  -4.750  -0.2018   0.07345   0.06689  -0.0395   1.0000   0.0758
  -4.500  -0.1742   0.07190   0.06532  -0.0452   1.0000   0.0811
  -4.250  -0.1531   0.06934   0.06280  -0.0484   1.0000   0.0833
  -4.000  -0.1472   0.06638   0.05995  -0.0465   1.0000   0.0867
  -3.500  -0.0984   0.06188   0.05548  -0.0533   1.0000   0.0980
  -3.250  -0.0809   0.05953   0.05320  -0.0541   1.0000   0.1046
  -3.000  -0.0463   0.05746   0.05109  -0.0597   1.0000   0.1117
  -2.750  -0.0209   0.05470   0.04840  -0.0617   0.9977   0.1194
  -2.500   0.0871   0.04959   0.04312  -0.0812   0.9730   0.1420
  -2.250   0.1739   0.04528   0.03872  -0.0948   0.9460   0.1724
  -2.000   0.2212   0.04128   0.03483  -0.0995   0.9248   0.1953
  -1.000   0.4050   0.03334   0.02472  -0.1100   0.5624   0.1391
  -0.500   0.4652   0.03306   0.02138  -0.1108   0.0648   0.0751
  -0.250   0.5001   0.03196   0.02003  -0.1116   0.0613   0.0666
   0.000   0.5352   0.03113   0.01881  -0.1121   0.0588   0.0602
   0.250   0.5652   0.03036   0.01800  -0.1124   0.0569   0.0581
   0.500   0.5951   0.02989   0.01738  -0.1123   0.0554   0.0561
   0.750   0.6249   0.02960   0.01692  -0.1122   0.0544   0.0556
   1.000   0.6537   0.02947   0.01661  -0.1118   0.0531   0.0566
   1.250   0.6807   0.02947   0.01643  -0.1109   0.0513   0.0577
   1.500   0.7063   0.02961   0.01641  -0.1099   0.0494   0.0580
   1.750   0.7309   0.02990   0.01658  -0.1087   0.0480   0.0585
   2.000   0.7553   0.03034   0.01692  -0.1075   0.0474   0.0594
   2.250   0.7803   0.03086   0.01740  -0.1063   0.0473   0.0621
   2.500   0.8064   0.03153   0.01802  -0.1052   0.0473   0.0681
   2.750   0.8342   0.03228   0.01874  -0.1042   0.0475   0.0748
   3.000   0.8631   0.03318   0.01964  -0.1033   0.0478   0.0863
   3.250   0.8888   0.03295   0.02079  -0.1022   0.0482   1.0000
   3.500   0.9176   0.03442   0.02201  -0.1012   0.0487   1.0000
   3.750   0.9460   0.03606   0.02356  -0.1004   0.0495   1.0000
   4.000   0.9737   0.03788   0.02539  -0.0995   0.0504   1.0000
   4.250   1.0007   0.03987   0.02744  -0.0986   0.0514   1.0000
   4.500   1.0269   0.04209   0.02975  -0.0978   0.0524   1.0000
   4.750   1.0523   0.04460   0.03234  -0.0970   0.0535   1.0000
   5.000   1.0769   0.04771   0.03544  -0.0964   0.0546   1.0000
   5.250   1.1010   0.04901   0.03740  -0.0946   0.0571   1.0000
   5.500   1.1229   0.05160   0.04042  -0.0932   0.0587   1.0000
   5.750   1.1429   0.05449   0.04367  -0.0919   0.0598   1.0000
   6.000   1.1611   0.05761   0.04712  -0.0906   0.0608   1.0000
   6.250   1.1778   0.06102   0.05083  -0.0894   0.0621   1.0000
   6.500   1.1935   0.06495   0.05498  -0.0884   0.0639   1.0000
   6.750   1.2076   0.06825   0.05900  -0.0864   0.0721   1.0000
   7.000   1.2226   0.07344   0.06419  -0.0857   0.0768   1.0000
   7.250   1.1420   0.07029   0.06244  -0.0727   0.0846   1.0000
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