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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 100,000
Max Cl/Cd: 59.92 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e212-il-100000.txt
Download as CSV file: xf-e212-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4094   0.10194   0.09692  -0.0316   1.0000   0.1230
  -8.750  -0.4162   0.09914   0.09420  -0.0325   1.0000   0.1274
  -8.500  -0.4771   0.09793   0.09329  -0.0375   1.0000   0.1303
  -8.250  -0.4285   0.09267   0.08789  -0.0326   1.0000   0.1334
  -8.000  -0.4235   0.09017   0.08542  -0.0310   1.0000   0.1370
  -7.750  -0.4352   0.08766   0.08301  -0.0306   1.0000   0.1410
  -7.500  -0.4956   0.08437   0.08000  -0.0376   1.0000   0.1445
  -7.250  -0.5309   0.06010   0.05547  -0.0522   1.0000   0.0721
  -7.000  -0.5455   0.04815   0.04273  -0.0596   1.0000   0.0608
  -6.750  -0.5349   0.04320   0.03745  -0.0609   1.0000   0.0587
  -6.500  -0.5183   0.03788   0.03155  -0.0629   1.0000   0.0566
  -6.250  -0.4967   0.03420   0.02732  -0.0642   1.0000   0.0573
  -6.000  -0.4725   0.03124   0.02383  -0.0651   1.0000   0.0587
  -5.750  -0.4463   0.02858   0.02067  -0.0656   1.0000   0.0595
  -5.500  -0.4192   0.02639   0.01806  -0.0658   1.0000   0.0608
  -5.250  -0.3925   0.02463   0.01594  -0.0657   1.0000   0.0629
  -5.000  -0.3673   0.02285   0.01424  -0.0657   1.0000   0.0674
  -4.750  -0.3415   0.02170   0.01297  -0.0655   1.0000   0.0764
  -4.500  -0.3146   0.02034   0.01177  -0.0658   1.0000   0.0939
  -4.250  -0.2837   0.01870   0.01052  -0.0672   1.0000   0.1628
  -4.000  -0.2574   0.01831   0.01029  -0.0679   1.0000   0.2327
  -3.750  -0.2326   0.01807   0.01026  -0.0680   1.0000   0.2865
  -3.500  -0.2082   0.01786   0.01015  -0.0679   1.0000   0.3317
  -3.250  -0.1845   0.01775   0.01012  -0.0676   1.0000   0.3742
  -3.000  -0.1612   0.01773   0.01014  -0.0672   1.0000   0.4158
  -2.750  -0.1392   0.01775   0.01029  -0.0665   1.0000   0.4526
  -2.500  -0.1172   0.01782   0.01043  -0.0658   1.0000   0.4896
  -2.250  -0.0961   0.01794   0.01060  -0.0650   1.0000   0.5250
  -2.000  -0.0758   0.01809   0.01084  -0.0640   1.0000   0.5583
  -1.750  -0.0561   0.01828   0.01113  -0.0630   1.0000   0.5917
  -1.500  -0.0183   0.01870   0.01159  -0.0652   0.9933   0.6332
  -1.250   0.0224   0.01911   0.01208  -0.0677   0.9849   0.6737
  -1.000   0.0595   0.01934   0.01239  -0.0694   0.9750   0.7123
  -0.750   0.0941   0.01952   0.01262  -0.0706   0.9648   0.7502
  -0.500   0.1273   0.01963   0.01279  -0.0713   0.9546   0.7885
  -0.250   0.1609   0.01968   0.01289  -0.0720   0.9451   0.8297
   0.000   0.1893   0.01954   0.01282  -0.0714   0.9345   0.8743
   0.250   0.2148   0.01918   0.01256  -0.0704   0.9225   0.9383
   0.500   0.2671   0.01900   0.01230  -0.0760   0.9115   1.0000
   0.750   0.3242   0.01895   0.01212  -0.0821   0.9049   1.0000
   1.000   0.3656   0.01891   0.01200  -0.0851   0.8928   1.0000
   1.250   0.4076   0.01883   0.01187  -0.0880   0.8814   1.0000
   1.500   0.4618   0.01843   0.01145  -0.0925   0.8750   1.0000
   1.750   0.5016   0.01820   0.01121  -0.0945   0.8628   1.0000
   2.000   0.5434   0.01788   0.01089  -0.0967   0.8512   1.0000
   2.250   0.5906   0.01742   0.01047  -0.0996   0.8413   1.0000
   2.500   0.6393   0.01684   0.00993  -0.1026   0.8315   1.0000
   2.750   0.6791   0.01647   0.00960  -0.1040   0.8174   1.0000
   3.000   0.7193   0.01609   0.00925  -0.1055   0.8021   1.0000
   3.250   0.7575   0.01578   0.00898  -0.1065   0.7850   1.0000
   3.500   0.7887   0.01568   0.00890  -0.1064   0.7636   1.0000
   3.750   0.8238   0.01551   0.00872  -0.1069   0.7425   1.0000
   4.000   0.8530   0.01553   0.00876  -0.1065   0.7180   1.0000
   4.250   0.8834   0.01556   0.00876  -0.1062   0.6931   1.0000
   4.500   0.9114   0.01569   0.00883  -0.1055   0.6661   1.0000
   4.750   0.9369   0.01589   0.00902  -0.1045   0.6371   1.0000
   5.000   0.9617   0.01615   0.00922  -0.1034   0.6070   1.0000
   5.250   0.9857   0.01646   0.00946  -0.1021   0.5760   1.0000
   5.500   1.0084   0.01683   0.00977  -0.1007   0.5436   1.0000
   5.750   1.0297   0.01725   0.01014  -0.0992   0.5094   1.0000
   6.000   1.0503   0.01773   0.01054  -0.0975   0.4744   1.0000
   6.250   1.0702   0.01829   0.01095  -0.0958   0.4389   1.0000
   6.500   1.0883   0.01889   0.01151  -0.0939   0.4003   1.0000
   6.750   1.1057   0.01961   0.01208  -0.0919   0.3623   1.0000
   7.000   1.1219   0.02040   0.01276  -0.0898   0.3227   1.0000
   7.250   1.1373   0.02135   0.01356  -0.0877   0.2840   1.0000
   7.500   1.1513   0.02242   0.01443  -0.0855   0.2465   1.0000
   7.750   1.1641   0.02351   0.01541  -0.0832   0.2086   1.0000
   8.000   1.1747   0.02465   0.01633  -0.0808   0.1734   1.0000
   8.250   1.1859   0.02591   0.01748  -0.0785   0.1395   1.0000
   8.500   1.1945   0.02754   0.01896  -0.0758   0.1090   1.0000
   8.750   1.1996   0.02968   0.02092  -0.0726   0.0828   1.0000
   9.000   1.2071   0.03189   0.02300  -0.0697   0.0682   1.0000
   9.250   1.2212   0.03399   0.02514  -0.0677   0.0591   1.0000
   9.500   1.2397   0.03641   0.02753  -0.0668   0.0533   1.0000
   9.750   1.2628   0.03873   0.03007  -0.0660   0.0495   1.0000
  10.000   1.2859   0.04127   0.03272  -0.0656   0.0469   1.0000
  10.250   1.3135   0.04497   0.03648  -0.0661   0.0449   1.0000
  10.500   1.3310   0.04903   0.04088  -0.0651   0.0441   1.0000
  10.750   1.3361   0.05193   0.04422  -0.0624   0.0435   1.0000
  11.000   1.3356   0.05493   0.04765  -0.0593   0.0429   1.0000
  11.250   1.3291   0.05792   0.05105  -0.0558   0.0425   1.0000
  11.500   1.3186   0.06111   0.05459  -0.0523   0.0421   1.0000
  11.750   1.3050   0.06461   0.05841  -0.0492   0.0420   1.0000
  12.000   1.2886   0.06846   0.06258  -0.0468   0.0419   1.0000
  12.250   1.2700   0.07277   0.06717  -0.0452   0.0421   1.0000
  12.500   1.2494   0.07758   0.07225  -0.0446   0.0422   1.0000
  12.750   1.2274   0.08297   0.07789  -0.0451   0.0425   1.0000
  13.000   1.2043   0.08902   0.08416  -0.0468   0.0428   1.0000
  13.250   1.1808   0.09575   0.09105  -0.0496   0.0432   1.0000
  13.500   1.1581   0.10317   0.09864  -0.0533   0.0436   1.0000
  13.750   1.1375   0.11111   0.10669  -0.0576   0.0441   1.0000
  14.000   0.8630   0.13633   0.13273  -0.0716   0.0543   1.0000
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