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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 200,000
Max Cl/Cd: 34.33 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel10-il-200000-n5.txt
Download as CSV file: xf-eiffel10-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3856   0.10595   0.10211  -0.0090   1.0000   0.0136
  -8.250  -0.3774   0.10316   0.09935  -0.0101   1.0000   0.0137
  -8.000  -0.3692   0.10050   0.09671  -0.0112   1.0000   0.0138
  -7.750  -0.3605   0.09786   0.09412  -0.0126   1.0000   0.0139
  -7.500  -0.3492   0.09510   0.09139  -0.0146   1.0000   0.0140
  -7.250  -0.3370   0.09233   0.08866  -0.0167   1.0000   0.0142
  -7.000  -0.3241   0.08957   0.08593  -0.0191   1.0000   0.0143
  -6.750  -0.3107   0.08684   0.08324  -0.0214   1.0000   0.0144
  -6.500  -0.2973   0.08418   0.08062  -0.0237   1.0000   0.0146
  -6.250  -0.2852   0.08168   0.07818  -0.0255   1.0000   0.0147
  -6.000  -0.2672   0.07885   0.07538  -0.0288   0.9971   0.0149
  -5.750  -0.2302   0.07481   0.07131  -0.0366   0.9863   0.0152
  -5.500  -0.1884   0.07067   0.06713  -0.0452   0.9669   0.0156
  -5.250  -0.1454   0.06678   0.06314  -0.0537   0.9330   0.0158
  -5.000  -0.1071   0.06351   0.05977  -0.0609   0.9081   0.0159
  -4.750  -0.0741   0.06033   0.05651  -0.0663   0.8881   0.0161
  -4.500  -0.0573   0.05740   0.05350  -0.0665   0.8587   0.0164
  -4.250  -0.0330   0.05489   0.05077  -0.0687   0.8098   0.0170
  -4.000  -0.0036   0.05232   0.04795  -0.0720   0.7616   0.0176
  -3.750   0.0294   0.04969   0.04509  -0.0760   0.7188   0.0181
  -3.500   0.0641   0.04747   0.04230  -0.0799   0.6104   0.0185
  -3.250   0.0974   0.04749   0.04026  -0.0845   0.0356   0.0187
  -2.750   0.1642   0.04234   0.03499  -0.0910   0.0313   0.0193
  -2.500   0.1992   0.04010   0.03269  -0.0942   0.0303   0.0199
  -2.250   0.2371   0.03793   0.03043  -0.0976   0.0280   0.0208
  -2.000   0.2811   0.03578   0.02812  -0.1016   0.0258   0.0217
  -1.750   0.3170   0.03370   0.02597  -0.1042   0.0251   0.0222
  -1.500   0.3497   0.03206   0.02428  -0.1062   0.0246   0.0234
  -1.250   0.3932   0.03018   0.02213  -0.1088   0.0243   0.0253
  -1.000   0.4220   0.02894   0.02091  -0.1102   0.0241   0.0278
  -0.750   0.4588   0.02761   0.01937  -0.1118   0.0240   0.0339
  -0.500   0.4905   0.02669   0.01832  -0.1129   0.0240   0.0395
  -0.250   0.5217   0.02594   0.01742  -0.1137   0.0242   0.0461
   0.250   0.5818   0.02576   0.01684  -0.1142   0.0248   0.0700
   1.000   0.6757   0.02325   0.01349  -0.1139   0.0260   0.0323
   1.250   0.7042   0.02333   0.01330  -0.1134   0.0266   0.0267
   1.500   0.7326   0.02345   0.01320  -0.1128   0.0274   0.0242
   1.750   0.7612   0.02348   0.01324  -0.1121   0.0283   0.0257
   2.000   0.7880   0.02447   0.01399  -0.1117   0.0272   0.0259
   2.250   0.8155   0.02489   0.01451  -0.1110   0.0261   0.0252
   2.500   0.8445   0.02556   0.01536  -0.1101   0.0298   0.0251
   2.750   0.8740   0.02736   0.01723  -0.1093   0.0372   0.0253
   4.250   1.0292   0.03468   0.02691  -0.1040   0.0366   1.0000
   5.250   1.0736   0.03127   0.02459  -0.0923   0.0287   1.0000
   5.500   1.0912   0.03393   0.02735  -0.0912   0.0280   1.0000
   5.750   1.1071   0.03708   0.03054  -0.0903   0.0274   1.0000
   6.250   1.1338   0.04414   0.03832  -0.0863   0.0259   1.0000
   6.500   1.1453   0.04769   0.04214  -0.0843   0.0252   1.0000
   6.750   1.1543   0.05149   0.04616  -0.0824   0.0247   1.0000
   7.000   1.1606   0.05545   0.05033  -0.0805   0.0243   1.0000
   7.250   1.1643   0.05953   0.05460  -0.0786   0.0240   1.0000
   7.500   1.1649   0.06369   0.05894  -0.0765   0.0238   1.0000
   7.750   1.1620   0.06793   0.06334  -0.0743   0.0236   1.0000
   8.000   1.1548   0.07217   0.06774  -0.0720   0.0235   1.0000
   8.250   1.1419   0.07636   0.07211  -0.0694   0.0235   1.0000
   8.500   1.1182   0.08019   0.07607  -0.0659   0.0235   1.0000
   8.750   1.0887   0.08482   0.08087  -0.0639   0.0236   1.0000
   9.000   1.0555   0.09076   0.08697  -0.0641   0.0238   1.0000
   9.250   1.0207   0.09822   0.09460  -0.0666   0.0241   1.0000
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