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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 1,000,000
Max Cl/Cd: 45.24 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel10-il-1000000-n5.txt
Download as CSV file: xf-eiffel10-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5480   0.16059   0.15875   0.0196   1.0000   0.0064
 -13.000  -0.5404   0.15750   0.15567   0.0182   1.0000   0.0065
 -12.750  -0.5329   0.15439   0.15256   0.0169   1.0000   0.0067
 -12.500  -0.5252   0.15123   0.14940   0.0155   1.0000   0.0069
 -12.250  -0.5176   0.14808   0.14625   0.0142   1.0000   0.0071
 -12.000  -0.5101   0.14495   0.14312   0.0129   1.0000   0.0071
 -11.750  -0.5023   0.14183   0.14000   0.0116   1.0000   0.0072
 -11.500  -0.4945   0.13874   0.13692   0.0102   1.0000   0.0072
 -11.250  -0.4867   0.13569   0.13387   0.0089   1.0000   0.0072
 -11.000  -0.4788   0.13265   0.13083   0.0076   1.0000   0.0072
 -10.750  -0.4708   0.12963   0.12782   0.0062   1.0000   0.0072
 -10.500  -0.4626   0.12663   0.12483   0.0048   1.0000   0.0073
 -10.250  -0.4544   0.12365   0.12185   0.0035   1.0000   0.0073
 -10.000  -0.4462   0.12070   0.11891   0.0021   1.0000   0.0073
  -9.750  -0.4379   0.11775   0.11597   0.0007   1.0000   0.0073
  -9.500  -0.4295   0.11484   0.11306  -0.0007   1.0000   0.0073
  -9.250  -0.4209   0.11193   0.11016  -0.0021   1.0000   0.0073
  -9.000  -0.4122   0.10904   0.10729  -0.0036   1.0000   0.0073
  -8.750  -0.4035   0.10619   0.10444  -0.0051   1.0000   0.0073
  -8.500  -0.3948   0.10335   0.10162  -0.0067   1.0000   0.0073
  -8.250  -0.3864   0.10058   0.09887  -0.0082   1.0000   0.0073
  -8.000  -0.3775   0.09782   0.09613  -0.0100   1.0000   0.0073
  -7.750  -0.3563   0.09402   0.09228  -0.0153   0.9467   0.0073
  -7.500  -0.3493   0.09146   0.08948  -0.0153   0.8798   0.0074
  -7.250  -0.3364   0.08876   0.08665  -0.0173   0.8462   0.0075
  -7.000  -0.3208   0.08598   0.08377  -0.0201   0.8219   0.0075
  -6.750  -0.3034   0.08317   0.08086  -0.0232   0.7974   0.0076
  -6.500  -0.2848   0.08041   0.07792  -0.0265   0.7529   0.0078
  -6.250  -0.2646   0.07765   0.07492  -0.0301   0.6948   0.0079
  -6.000  -0.2454   0.07690   0.07235  -0.0339   0.0258   0.0081
  -5.750  -0.2218   0.07390   0.06932  -0.0380   0.0225   0.0084
  -5.500  -0.1965   0.07085   0.06625  -0.0423   0.0211   0.0086
  -5.250  -0.1696   0.06777   0.06314  -0.0468   0.0200   0.0087
  -5.000  -0.1408   0.06469   0.06004  -0.0515   0.0190   0.0088
  -4.750  -0.1103   0.06160   0.05692  -0.0563   0.0187   0.0089
  -4.500  -0.0778   0.05852   0.05379  -0.0613   0.0184   0.0089
  -4.250  -0.0436   0.05544   0.05067  -0.0664   0.0182   0.0090
  -4.000  -0.0075   0.05236   0.04753  -0.0716   0.0174   0.0090
  -3.750   0.0310   0.04926   0.04435  -0.0770   0.0164   0.0091
  -3.500   0.0732   0.04607   0.04106  -0.0829   0.0158   0.0091
  -3.250   0.1141   0.04319   0.03808  -0.0879   0.0152   0.0091
  -2.750   0.1778   0.03826   0.03304  -0.0939   0.0140   0.0093
  -2.500   0.2119   0.03630   0.03102  -0.0968   0.0134   0.0096
  -2.250   0.2484   0.03427   0.02891  -0.0999   0.0132   0.0098
  -2.000   0.2856   0.03226   0.02680  -0.1029   0.0129   0.0100
  -1.750   0.3226   0.03035   0.02480  -0.1055   0.0128   0.0102
  -1.500   0.3596   0.02855   0.02288  -0.1078   0.0128   0.0105
  -1.250   0.3977   0.02677   0.02097  -0.1099   0.0128   0.0109
  -0.250   0.5416   0.02047   0.01398  -0.1149   0.0133   0.0111
   0.250   0.6034   0.01883   0.01202  -0.1164   0.0126   0.0117
   0.750   0.6620   0.01873   0.01144  -0.1160   0.0120   0.0134
   1.000   0.6901   0.01907   0.01161  -0.1158   0.0119   0.0134
   1.500   0.7498   0.01763   0.01002  -0.1159   0.0116   0.0109
   1.750   0.7780   0.01768   0.01002  -0.1156   0.0113   0.0110
   2.000   0.8060   0.01791   0.01024  -0.1152   0.0109   0.0113
   2.250   0.8334   0.01842   0.01080  -0.1147   0.0104   0.0117
   2.500   0.8607   0.01905   0.01147  -0.1143   0.0100   0.0122
   2.750   0.8877   0.01981   0.01226  -0.1138   0.0098   0.0132
   3.000   0.9148   0.02062   0.01313  -0.1134   0.0096   0.0137
   3.250   0.9418   0.02167   0.01427  -0.1129   0.0096   0.0140
   3.500   0.9686   0.02312   0.01586  -0.1122   0.0096   0.0144
   3.750   0.9956   0.02557   0.01857  -0.1110   0.0101   0.0152
   4.000   1.0211   0.02769   0.02089  -0.1100   0.0107   0.0159
   4.250   1.0443   0.02993   0.02330  -0.1093   0.0115   0.0175
   4.500   1.0656   0.03268   0.02614  -0.1088   0.0117   0.0183
   4.750   1.0882   0.03484   0.02846  -0.1079   0.0118   0.0194
   5.000   1.1101   0.03705   0.03084  -0.1068   0.0118   0.0208
   5.250   1.1311   0.03937   0.03334  -0.1057   0.0118   0.0242
   5.750   1.1690   0.04302   0.03883  -0.1034   0.0118   1.0000
   7.500   1.1909   0.05773   0.05500  -0.0817   0.0117   1.0000
   7.750   1.1900   0.06202   0.05945  -0.0792   0.0117   1.0000
   8.000   1.1849   0.06633   0.06391  -0.0766   0.0117   1.0000
   8.250   1.1744   0.07064   0.06837  -0.0737   0.0116   1.0000
   8.500   1.1540   0.07438   0.07223  -0.0698   0.0116   1.0000
   8.750   1.1254   0.07820   0.07615  -0.0663   0.0116   1.0000
   9.000   1.0950   0.08302   0.08108  -0.0648   0.0116   1.0000
   9.250   1.0642   0.08886   0.08702  -0.0652   0.0117   1.0000
   9.500   1.0330   0.09585   0.09410  -0.0674   0.0117   1.0000
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