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E207 (12.04%) (e207-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E207 (12.04%) (e207-il)
Reynolds number: 50,000
Max Cl/Cd: 30.89 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e207-il-50000.txt
Download as CSV file: xf-e207-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E207  (12.04%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4077   0.11327   0.10645  -0.0169   1.0000   0.2698
  -9.250  -0.3787   0.10748   0.10062  -0.0157   1.0000   0.2793
  -8.750  -0.3982   0.10369   0.09705  -0.0166   1.0000   0.2994
  -8.500  -0.3691   0.09822   0.09154  -0.0155   1.0000   0.3093
  -8.250  -0.3648   0.09508   0.08846  -0.0151   1.0000   0.3207
  -8.000  -0.3629   0.09222   0.08567  -0.0146   1.0000   0.3339
  -7.500  -0.3720   0.08739   0.08104  -0.0131   1.0000   0.3596
  -7.250  -0.4655   0.07142   0.06538  -0.0359   1.0000   0.1743
  -7.000  -0.4934   0.06345   0.05727  -0.0401   1.0000   0.1479
  -6.750  -0.5095   0.05755   0.05108  -0.0408   1.0000   0.1355
  -6.500  -0.5114   0.05326   0.04662  -0.0396   1.0000   0.1299
  -6.250  -0.5187   0.04866   0.04133  -0.0381   1.0000   0.1229
  -6.000  -0.5133   0.04551   0.03799  -0.0361   1.0000   0.1213
  -5.750  -0.5078   0.04259   0.03471  -0.0340   1.0000   0.1206
  -5.500  -0.5011   0.04004   0.03170  -0.0320   1.0000   0.1218
  -5.250  -0.4917   0.03779   0.02895  -0.0300   1.0000   0.1234
  -5.000  -0.4796   0.03556   0.02651  -0.0284   1.0000   0.1261
  -4.750  -0.4652   0.03373   0.02452  -0.0269   1.0000   0.1293
  -4.500  -0.4492   0.03203   0.02251  -0.0254   1.0000   0.1337
  -4.250  -0.4320   0.03051   0.02069  -0.0242   1.0000   0.1411
  -4.000  -0.4148   0.02933   0.01937  -0.0229   1.0000   0.1541
  -3.750  -0.3971   0.02804   0.01813  -0.0217   1.0000   0.1712
  -3.500  -0.3801   0.02684   0.01709  -0.0204   1.0000   0.2051
  -3.250  -0.3630   0.02557   0.01619  -0.0193   1.0000   0.2710
  -3.000  -0.3489   0.02431   0.01579  -0.0174   1.0000   0.3880
  -2.750  -0.3285   0.02361   0.01619  -0.0150   0.9939   0.5820
  -2.500  -0.3038   0.02367   0.01676  -0.0121   0.9827   0.7279
  -2.250  -0.2718   0.02400   0.01733  -0.0097   0.9720   0.8540
  -2.000  -0.0701   0.02565   0.01795  -0.0396   0.9710   1.0000
  -1.750  -0.0493   0.02531   0.01734  -0.0429   0.9545   1.0000
  -1.500  -0.0240   0.02535   0.01704  -0.0456   0.9398   1.0000
  -1.250   0.0114   0.02566   0.01701  -0.0491   0.9274   1.0000
  -1.000   0.0394   0.02604   0.01711  -0.0508   0.9148   1.0000
  -0.750   0.0665   0.02651   0.01730  -0.0521   0.9025   1.0000
  -0.500   0.0940   0.02704   0.01761  -0.0532   0.8912   1.0000
  -0.250   0.1280   0.02758   0.01795  -0.0553   0.8807   1.0000
   0.000   0.1610   0.02815   0.01832  -0.0571   0.8705   1.0000
   0.250   0.1799   0.02882   0.01885  -0.0566   0.8593   1.0000
   0.500   0.2064   0.02950   0.01938  -0.0573   0.8493   1.0000
   0.750   0.2441   0.03009   0.01985  -0.0597   0.8403   1.0000
   1.000   0.2554   0.03097   0.02062  -0.0579   0.8296   1.0000
   1.250   0.2801   0.03177   0.02133  -0.0583   0.8206   1.0000
   1.500   0.3103   0.03250   0.02198  -0.0594   0.8116   1.0000
   1.750   0.3196   0.03356   0.02297  -0.0575   0.8017   1.0000
   2.000   0.3545   0.03430   0.02367  -0.0592   0.7937   1.0000
   2.250   0.3642   0.03543   0.02474  -0.0575   0.7838   1.0000
   2.500   0.3799   0.03656   0.02583  -0.0566   0.7752   1.0000
   2.750   0.4110   0.03741   0.02669  -0.0577   0.7667   1.0000
   3.000   0.4133   0.03886   0.02810  -0.0553   0.7576   1.0000
   3.250   0.4473   0.03974   0.02899  -0.0567   0.7494   1.0000
   3.500   0.4501   0.04127   0.03050  -0.0545   0.7401   1.0000
   3.750   0.4674   0.04257   0.03182  -0.0540   0.7315   1.0000
   4.000   0.4939   0.04365   0.03295  -0.0544   0.7224   1.0000
   4.250   0.4950   0.04541   0.03470  -0.0524   0.7134   1.0000
   4.500   0.5229   0.04654   0.03589  -0.0529   0.7039   1.0000
   4.750   0.5352   0.04806   0.03745  -0.0520   0.6941   1.0000
   5.000   0.5428   0.04977   0.03919  -0.0507   0.6841   1.0000
   5.250   0.5673   0.05104   0.04056  -0.0508   0.6735   1.0000
   5.500   0.5989   0.05204   0.04167  -0.0512   0.6620   1.0000
   5.750   0.5968   0.05413   0.04379  -0.0493   0.6506   1.0000
   6.000   0.6081   0.05585   0.04558  -0.0484   0.6385   1.0000
   6.250   0.6251   0.05737   0.04721  -0.0478   0.6256   1.0000
   6.500   0.6438   0.05880   0.04876  -0.0471   0.6118   1.0000
   6.750   0.6622   0.06023   0.05029  -0.0464   0.5974   1.0000
   7.000   0.6795   0.06166   0.05184  -0.0456   0.5822   1.0000
   7.250   0.6967   0.06308   0.05341  -0.0446   0.5663   1.0000
   7.500   0.7174   0.06420   0.05468  -0.0436   0.5492   1.0000
   7.750   0.7531   0.06420   0.05490  -0.0426   0.5311   1.0000
   8.000   0.7849   0.06422   0.05513  -0.0412   0.5129   1.0000
   8.250   0.7836   0.06664   0.05763  -0.0397   0.4946   1.0000
   8.500   0.8125   0.06645   0.05770  -0.0379   0.4746   1.0000
   8.750   0.8614   0.06381   0.05538  -0.0350   0.4532   1.0000
   9.000   1.0655   0.04284   0.03535  -0.0307   0.4087   1.0000
   9.250   1.1152   0.03829   0.03081  -0.0278   0.3641   1.0000
   9.500   1.1364   0.03691   0.02920  -0.0242   0.3203   1.0000
   9.750   1.1472   0.03714   0.02909  -0.0206   0.2799   1.0000
  10.000   1.1521   0.03845   0.03011  -0.0171   0.2456   1.0000
  10.250   1.1635   0.04023   0.03143  -0.0147   0.2130   1.0000
  10.500   1.1654   0.04262   0.03390  -0.0118   0.1901   1.0000
  10.750   1.1738   0.04512   0.03623  -0.0096   0.1675   1.0000
  11.000   1.1786   0.04777   0.03891  -0.0073   0.1498   1.0000
  11.250   1.1845   0.05050   0.04164  -0.0052   0.1346   1.0000
  11.750   1.1893   0.05674   0.04807  -0.0012   0.1137   1.0000
  12.000   1.2038   0.06025   0.05151  -0.0005   0.1033   1.0000
  12.250   1.1846   0.06362   0.05529   0.0024   0.1018   1.0000
  12.500   1.1655   0.06748   0.05949   0.0042   0.1005   1.0000
  12.750   1.1453   0.07185   0.06417   0.0050   0.0999   1.0000
  13.000   1.1214   0.07686   0.06944   0.0048   0.0997   1.0000
  13.250   1.0977   0.08249   0.07530   0.0036   0.1006   1.0000
  13.500   1.0698   0.08902   0.08202   0.0013   0.1014   1.0000
  13.750   1.0438   0.09618   0.08931  -0.0017   0.1025   1.0000
  14.000   1.0204   0.10381   0.09704  -0.0051   0.1035   1.0000
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