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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 500,000
Max Cl/Cd: 32.43 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel10-il-500000.txt
Download as CSV file: xf-eiffel10-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5835   0.16989   0.16726   0.0292   1.0000   0.0108
 -13.500  -0.5758   0.16677   0.16414   0.0278   1.0000   0.0109
 -13.250  -0.5681   0.16367   0.16104   0.0264   1.0000   0.0110
 -13.000  -0.5603   0.16054   0.15792   0.0250   1.0000   0.0111
 -12.750  -0.5526   0.15743   0.15481   0.0237   1.0000   0.0111
 -12.500  -0.5449   0.15434   0.15172   0.0223   1.0000   0.0112
 -12.250  -0.5372   0.15126   0.14865   0.0210   1.0000   0.0112
 -12.000  -0.5294   0.14818   0.14557   0.0196   1.0000   0.0112
 -11.750  -0.5216   0.14513   0.14252   0.0182   1.0000   0.0112
 -11.500  -0.5139   0.14211   0.13951   0.0167   1.0000   0.0113
 -11.250  -0.5061   0.13913   0.13653   0.0152   1.0000   0.0113
  -9.000  -0.4353   0.11374   0.11124   0.0007   1.0000   0.0114
  -8.750  -0.4258   0.10998   0.10749   0.0005   1.0000   0.0114
  -8.500  -0.4169   0.10676   0.10429  -0.0002   1.0000   0.0114
  -8.250  -0.4083   0.10379   0.10134  -0.0012   1.0000   0.0114
  -8.000  -0.3997   0.10095   0.09853  -0.0023   1.0000   0.0115
  -7.750  -0.3908   0.09822   0.09582  -0.0036   1.0000   0.0115
  -7.500  -0.3797   0.09537   0.09299  -0.0056   1.0000   0.0116
  -7.250  -0.3666   0.09245   0.09009  -0.0080   1.0000   0.0116
  -7.000  -0.3523   0.08951   0.08718  -0.0107   1.0000   0.0117
  -6.750  -0.3368   0.08656   0.08426  -0.0136   1.0000   0.0117
  -6.500  -0.3202   0.08361   0.08133  -0.0166   1.0000   0.0118
  -6.250  -0.3026   0.08066   0.07841  -0.0198   1.0000   0.0119
  -6.000  -0.2843   0.07775   0.07552  -0.0230   1.0000   0.0120
  -5.750  -0.2449   0.07352   0.07126  -0.0314   0.9650   0.0121
  -5.500  -0.2190   0.07035   0.06796  -0.0356   0.9100   0.0123
  -5.250  -0.1979   0.06761   0.06507  -0.0384   0.8705   0.0125
  -5.000  -0.1744   0.06483   0.06210  -0.0416   0.8268   0.0127
  -4.750  -0.1474   0.06193   0.05901  -0.0455   0.7899   0.0130
  -4.500  -0.1135   0.05901   0.05583  -0.0508   0.7406   0.0134
  -4.250  -0.0521   0.04009   0.03495  -0.0557   0.0370   0.0135
  -4.000  -0.0382   0.03697   0.03183  -0.0554   0.0320   0.0136
  -3.750  -0.0195   0.05257   0.04699  -0.0644   0.0304   0.0136
  -3.500   0.0074   0.04999   0.04440  -0.0669   0.0293   0.0138
  -3.250   0.0399   0.04751   0.04188  -0.0704   0.0288   0.0141
  -3.000   0.0749   0.04503   0.03936  -0.0741   0.0287   0.0144
  -2.750   0.1108   0.04261   0.03688  -0.0777   0.0289   0.0146
  -2.500   0.1472   0.04030   0.03450  -0.0812   0.0294   0.0148
  -2.250   0.1840   0.03811   0.03223  -0.0843   0.0301   0.0150
  -2.000   0.2214   0.03604   0.03007  -0.0873   0.0312   0.0153
  -1.750   0.2612   0.03410   0.02800  -0.0902   0.0322   0.0156
  -1.500   0.3031   0.03208   0.02579  -0.0928   0.0331   0.0158
  -1.250   0.3410   0.03011   0.02370  -0.0946   0.0356   0.0158
  -1.000   0.3685   0.02882   0.02239  -0.0960   0.0383   0.0161
  -0.750   0.4009   0.02762   0.02116  -0.0971   0.0416   0.0165
  -0.500   0.4347   0.02648   0.01995  -0.0980   0.0474   0.0170
   3.250   0.8828   0.02722   0.01929  -0.0963   0.0228   0.0361
   3.500   0.9099   0.02817   0.02037  -0.0957   0.0221   0.0314
   3.750   0.9361   0.02939   0.02168  -0.0954   0.0216   0.0287
   4.000   0.9611   0.03102   0.02336  -0.0950   0.0213   0.0274
   4.250   0.9855   0.03335   0.02567  -0.0948   0.0210   0.0270
   4.500   1.0088   0.03653   0.02891  -0.0943   0.0208   0.0274
   4.750   1.0347   0.03666   0.02970  -0.0919   0.0201   0.0295
   5.000   1.0553   0.03714   0.03194  -0.0906   0.0196   1.0000
   5.250   1.0772   0.03934   0.03430  -0.0895   0.0191   1.0000
   5.500   1.0977   0.04164   0.03674  -0.0885   0.0187   1.0000
   5.750   1.1168   0.04404   0.03927  -0.0875   0.0184   1.0000
   6.000   1.1345   0.04658   0.04192  -0.0865   0.0182   1.0000
   6.250   1.1509   0.04930   0.04475  -0.0856   0.0181   1.0000
   6.500   1.1658   0.05221   0.04776  -0.0847   0.0179   1.0000
   6.750   1.1795   0.05543   0.05104  -0.0839   0.0178   1.0000
   7.000   1.1923   0.05930   0.05493  -0.0832   0.0177   1.0000
   7.250   1.2033   0.06389   0.05957  -0.0824   0.0177   1.0000
   7.500   1.2075   0.06738   0.06339  -0.0804   0.0176   1.0000
   7.750   1.2084   0.07109   0.06743  -0.0782   0.0176   1.0000
   8.000   1.2026   0.07550   0.07228  -0.0755   0.0174   1.0000
   8.250   1.1941   0.08069   0.07780  -0.0738   0.0170   1.0000
   8.500   1.1805   0.08517   0.08244  -0.0725   0.0169   1.0000
   8.750   1.1584   0.08955   0.08693  -0.0715   0.0169   1.0000
   9.000   1.1356   0.09527   0.09276  -0.0736   0.0170   1.0000
   9.250   1.1140   0.10274   0.10033  -0.0787   0.0171   1.0000
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