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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 500,000
Max Cl/Cd: 38.4 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel10-il-500000-n5.txt
Download as CSV file: xf-eiffel10-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5364   0.15788   0.15529   0.0173   1.0000   0.0084
 -12.750  -0.5289   0.15478   0.15218   0.0159   1.0000   0.0085
 -12.500  -0.5212   0.15166   0.14907   0.0146   1.0000   0.0087
 -12.250  -0.5135   0.14856   0.14597   0.0132   1.0000   0.0088
 -12.000  -0.5058   0.14549   0.14290   0.0119   1.0000   0.0088
 -11.750  -0.4979   0.14242   0.13984   0.0105   1.0000   0.0089
 -11.500  -0.4900   0.13938   0.13680   0.0092   1.0000   0.0090
 -11.250  -0.4821   0.13636   0.13379   0.0078   1.0000   0.0090
 -11.000  -0.4741   0.13335   0.13079   0.0065   1.0000   0.0090
 -10.750  -0.4661   0.13036   0.12781   0.0051   1.0000   0.0090
 -10.500  -0.4580   0.12739   0.12485   0.0038   1.0000   0.0090
 -10.250  -0.4498   0.12444   0.12190   0.0024   1.0000   0.0090
 -10.000  -0.4416   0.12152   0.11899   0.0010   1.0000   0.0090
  -9.750  -0.4332   0.11862   0.11610  -0.0005   1.0000   0.0091
  -9.500  -0.4247   0.11575   0.11324  -0.0020   1.0000   0.0091
  -9.250  -0.4161   0.11291   0.11042  -0.0035   1.0000   0.0091
  -9.000  -0.4075   0.11011   0.10763  -0.0051   1.0000   0.0091
  -8.750  -0.3989   0.10736   0.10490  -0.0068   1.0000   0.0091
  -8.500  -0.3904   0.10467   0.10223  -0.0084   1.0000   0.0091
  -8.000  -0.3732   0.09909   0.09670  -0.0114   1.0000   0.0091
  -7.750  -0.3632   0.09590   0.09353  -0.0125   1.0000   0.0092
  -7.500  -0.3515   0.09296   0.09061  -0.0144   1.0000   0.0093
  -7.250  -0.3386   0.09011   0.08779  -0.0167   1.0000   0.0093
  -7.000  -0.3170   0.08676   0.08444  -0.0213   0.9820   0.0095
  -6.750  -0.2900   0.08314   0.08074  -0.0269   0.9277   0.0098
  -6.500  -0.2736   0.08040   0.07788  -0.0294   0.8923   0.0099
  -6.250  -0.2554   0.07759   0.07496  -0.0323   0.8625   0.0100
  -6.000  -0.2356   0.07478   0.07199  -0.0355   0.8280   0.0101
  -5.750  -0.2134   0.07187   0.06895  -0.0391   0.8006   0.0102
  -5.500  -0.1901   0.06905   0.06591  -0.0428   0.7568   0.0104
  -5.250  -0.1659   0.06644   0.06289  -0.0466   0.6643   0.0105
  -4.750  -0.1130   0.06276   0.05732  -0.0554   0.0252   0.0109
  -4.500  -0.0796   0.05969   0.05419  -0.0606   0.0239   0.0110
  -4.250  -0.0429   0.05660   0.05105  -0.0664   0.0231   0.0111
  -4.000  -0.0026   0.05348   0.04785  -0.0726   0.0226   0.0111
  -3.750   0.0395   0.05037   0.04465  -0.0789   0.0223   0.0111
  -3.500   0.0715   0.04737   0.04161  -0.0825   0.0218   0.0112
  -3.250   0.0966   0.04494   0.03917  -0.0844   0.0197   0.0114
  -3.000   0.1301   0.04269   0.03688  -0.0879   0.0187   0.0118
  -2.750   0.1671   0.04032   0.03444  -0.0917   0.0181   0.0121
  -2.500   0.2047   0.03805   0.03208  -0.0953   0.0174   0.0124
  -2.250   0.2427   0.03588   0.02981  -0.0987   0.0170   0.0127
  -2.000   0.2812   0.03382   0.02763  -0.1019   0.0166   0.0130
  -1.750   0.3215   0.03182   0.02548  -0.1048   0.0164   0.0133
  -1.500   0.3616   0.02986   0.02335  -0.1074   0.0163   0.0134
  -1.250   0.3999   0.02801   0.02132  -0.1094   0.0164   0.0134
  -1.000   0.4368   0.02626   0.01938  -0.1110   0.0164   0.0134
  -0.750   0.4676   0.02489   0.01794  -0.1126   0.0166   0.0137
  -0.500   0.4990   0.02395   0.01689  -0.1136   0.0169   0.0140
  -0.250   0.5314   0.02302   0.01581  -0.1144   0.0173   0.0148
   0.250   0.5946   0.02185   0.01409  -0.1151   0.0191   0.0167
   0.500   0.6243   0.02167   0.01374  -0.1152   0.0187   0.0174
   0.750   0.6566   0.02065   0.01257  -0.1150   0.0172   0.0187
   1.250   0.7130   0.02069   0.01216  -0.1150   0.0155   0.0193
   1.500   0.7409   0.02108   0.01241  -0.1147   0.0154   0.0196
   1.750   0.7693   0.02185   0.01302  -0.1143   0.0153   0.0147
   2.000   0.7982   0.02096   0.01235  -0.1137   0.0145   0.0146
   2.250   0.8259   0.02151   0.01293  -0.1131   0.0142   0.0150
   2.500   0.8534   0.02241   0.01385  -0.1125   0.0141   0.0163
   2.750   0.8808   0.02349   0.01505  -0.1119   0.0143   0.0174
   3.000   0.9070   0.02639   0.01773  -0.1120   0.0152   0.0174
   3.250   0.9336   0.02777   0.01923  -0.1115   0.0152   0.0176
   3.500   0.9598   0.02919   0.02080  -0.1109   0.0152   0.0181
   3.750   0.9855   0.03069   0.02246  -0.1103   0.0152   0.0191
   4.000   1.0106   0.03228   0.02423  -0.1096   0.0152   0.0215
   4.250   1.0350   0.03397   0.02609  -0.1088   0.0152   0.0223
   4.500   1.0586   0.03578   0.02810  -0.1078   0.0152   0.0237
   4.750   1.0814   0.03769   0.03023  -0.1068   0.0152   0.0274
   5.000   1.1010   0.03833   0.03256  -0.1055   0.0151   1.0000
   5.250   1.1221   0.04053   0.03496  -0.1043   0.0151   1.0000
   5.500   1.1423   0.04283   0.03747  -0.1029   0.0151   1.0000
   5.750   1.1614   0.04526   0.04012  -0.1015   0.0151   1.0000
   6.000   1.1796   0.04783   0.04294  -0.1000   0.0150   1.0000
   6.250   1.1967   0.05054   0.04587  -0.0983   0.0150   1.0000
   6.500   1.2158   0.05303   0.04867  -0.0962   0.0145   1.0000
   6.750   1.2312   0.05597   0.05183  -0.0945   0.0139   1.0000
   7.000   1.2429   0.05921   0.05525  -0.0929   0.0135   1.0000
   7.250   1.2522   0.06265   0.05888  -0.0912   0.0133   1.0000
   7.500   1.2589   0.06622   0.06264  -0.0896   0.0132   1.0000
   7.750   1.2628   0.06991   0.06651  -0.0879   0.0130   1.0000
   8.000   1.2635   0.07372   0.07048  -0.0861   0.0129   1.0000
   8.250   1.2605   0.07763   0.07455  -0.0844   0.0128   1.0000
   8.500   1.2531   0.08165   0.07871  -0.0827   0.0127   1.0000
   8.750   1.2392   0.08560   0.08279  -0.0807   0.0127   1.0000
   9.000   1.2171   0.08966   0.08697  -0.0787   0.0127   1.0000
   9.250   1.1936   0.09499   0.09242  -0.0795   0.0127   1.0000
   9.500   1.1696   0.10202   0.09957  -0.0831   0.0128   1.0000
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