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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 200,000
Max Cl/Cd: 84.86 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e214-il-200000-n5.txt
Download as CSV file: xf-e214-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E214  (11.1%)                                   
  
 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  -0.3444   0.08673   0.08335  -0.0501   0.9908   0.0187
  -8.250  -0.3408   0.08018   0.07683  -0.0563   0.9861   0.0181
  -7.750  -0.3621   0.04901   0.04536  -0.0909   0.9628   0.0163
  -7.500  -0.3536   0.04082   0.03660  -0.0993   0.9545   0.0164
  -7.250  -0.3358   0.03477   0.03001  -0.1044   0.9487   0.0168
  -7.000  -0.3060   0.03250   0.02754  -0.1077   0.9462   0.0177
  -6.750  -0.2851   0.03094   0.02581  -0.1081   0.9395   0.0188
  -6.500  -0.2557   0.02783   0.02221  -0.1106   0.9358   0.0198
  -6.250  -0.2227   0.02486   0.01870  -0.1132   0.9334   0.0203
  -6.000  -0.1955   0.02288   0.01633  -0.1138   0.9284   0.0209
  -5.750  -0.1659   0.02127   0.01440  -0.1147   0.9239   0.0215
  -5.500  -0.1323   0.02000   0.01284  -0.1161   0.9211   0.0227
  -5.250  -0.0981   0.01855   0.01130  -0.1179   0.9190   0.0241
  -5.000  -0.0720   0.01764   0.01029  -0.1178   0.9127   0.0248
  -4.750  -0.0400   0.01673   0.00929  -0.1188   0.9086   0.0257
  -4.500  -0.0044   0.01588   0.00834  -0.1205   0.9058   0.0269
  -4.250   0.0267   0.01521   0.00759  -0.1213   0.9007   0.0282
  -4.000   0.0581   0.01468   0.00696  -0.1221   0.8949   0.0300
  -3.750   0.0954   0.01399   0.00624  -0.1243   0.8914   0.0337
  -3.500   0.1260   0.01356   0.00572  -0.1249   0.8847   0.0373
  -3.250   0.1603   0.01305   0.00519  -0.1263   0.8789   0.0462
  -3.000   0.1950   0.01251   0.00474  -0.1279   0.8731   0.0797
  -2.750   0.2267   0.01203   0.00443  -0.1289   0.8653   0.1358
  -2.500   0.2609   0.01137   0.00417  -0.1307   0.8584   0.2441
  -2.250   0.2932   0.01074   0.00401  -0.1321   0.8501   0.3827
  -2.000   0.3240   0.01043   0.00401  -0.1328   0.8410   0.4979
  -1.750   0.3578   0.01029   0.00389  -0.1338   0.8328   0.5502
  -1.500   0.3870   0.01023   0.00383  -0.1339   0.8219   0.5829
  -1.000   0.4479   0.01014   0.00366  -0.1346   0.8007   0.6280
  -0.500   0.5069   0.01011   0.00354  -0.1349   0.7780   0.6661
  -0.250   0.5350   0.01012   0.00352  -0.1348   0.7662   0.6831
   0.000   0.5630   0.01014   0.00351  -0.1347   0.7546   0.6995
   0.250   0.5907   0.01017   0.00351  -0.1345   0.7432   0.7159
   0.500   0.6181   0.01021   0.00351  -0.1342   0.7319   0.7325
   0.750   0.6442   0.01026   0.00355  -0.1337   0.7201   0.7487
   1.000   0.6702   0.01031   0.00359  -0.1332   0.7086   0.7646
   1.250   0.6960   0.01037   0.00365  -0.1327   0.6974   0.7810
   1.500   0.7215   0.01044   0.00370  -0.1321   0.6865   0.7989
   1.750   0.7458   0.01050   0.00377  -0.1312   0.6752   0.8187
   2.250   0.7917   0.01059   0.00392  -0.1288   0.6530   0.8741
   2.500   0.8146   0.01059   0.00395  -0.1275   0.6423   0.9257
   2.750   0.8445   0.01068   0.00400  -0.1280   0.6307   1.0000
   3.000   0.8712   0.01085   0.00415  -0.1278   0.6185   1.0000
   3.250   0.8975   0.01104   0.00429  -0.1276   0.6061   1.0000
   3.500   0.9235   0.01123   0.00445  -0.1273   0.5934   1.0000
   3.750   0.9491   0.01143   0.00462  -0.1269   0.5804   1.0000
   4.000   0.9744   0.01164   0.00482  -0.1265   0.5671   1.0000
   4.250   0.9993   0.01187   0.00501  -0.1259   0.5529   1.0000
   4.500   1.0237   0.01210   0.00522  -0.1253   0.5379   1.0000
   4.750   1.0475   0.01235   0.00544  -0.1246   0.5217   1.0000
   5.000   1.0709   0.01262   0.00570  -0.1238   0.5045   1.0000
   5.250   1.0938   0.01291   0.00595  -0.1229   0.4872   1.0000
   5.500   1.1163   0.01321   0.00623  -0.1219   0.4693   1.0000
   5.750   1.1382   0.01354   0.00654  -0.1209   0.4492   1.0000
   6.000   1.1587   0.01392   0.00688  -0.1195   0.4272   1.0000
   6.250   1.1789   0.01432   0.00724  -0.1182   0.4035   1.0000
   6.500   1.1980   0.01477   0.00763  -0.1167   0.3788   1.0000
   6.750   1.2161   0.01528   0.00806  -0.1150   0.3528   1.0000
   7.000   1.2327   0.01585   0.00854  -0.1132   0.3238   1.0000
   7.250   1.2481   0.01649   0.00910  -0.1111   0.2931   1.0000
   7.500   1.2613   0.01719   0.00968  -0.1087   0.2619   1.0000
   7.750   1.2733   0.01797   0.01033  -0.1062   0.2310   1.0000
   8.000   1.2849   0.01881   0.01105  -0.1037   0.2018   1.0000
   8.250   1.2968   0.01966   0.01180  -0.1013   0.1762   1.0000
   8.500   1.3084   0.02055   0.01261  -0.0989   0.1538   1.0000
   8.750   1.3202   0.02144   0.01348  -0.0966   0.1340   1.0000
   9.000   1.3308   0.02242   0.01441  -0.0943   0.1165   1.0000
   9.250   1.3415   0.02342   0.01538  -0.0920   0.1006   1.0000
   9.500   1.3514   0.02447   0.01641  -0.0897   0.0859   1.0000
   9.750   1.3604   0.02562   0.01752  -0.0874   0.0719   1.0000
  10.000   1.3685   0.02685   0.01871  -0.0851   0.0591   1.0000
  10.250   1.3764   0.02812   0.01997  -0.0829   0.0485   1.0000
  10.500   1.3841   0.02945   0.02132  -0.0808   0.0410   1.0000
  10.750   1.3911   0.03087   0.02278  -0.0787   0.0340   1.0000
  11.000   1.3988   0.03229   0.02428  -0.0768   0.0287   1.0000
  11.250   1.4036   0.03399   0.02602  -0.0748   0.0242   1.0000
  11.500   1.4091   0.03569   0.02782  -0.0730   0.0204   1.0000
  11.750   1.4113   0.03776   0.02996  -0.0712   0.0174   1.0000
  12.000   1.4145   0.03983   0.03217  -0.0696   0.0151   1.0000
  12.250   1.4150   0.04223   0.03465  -0.0680   0.0136   1.0000
  12.500   1.4157   0.04471   0.03726  -0.0667   0.0123   1.0000
  12.750   1.4168   0.04723   0.03994  -0.0657   0.0113   1.0000
  13.000   1.4178   0.04986   0.04269  -0.0648   0.0105   1.0000
  13.250   1.4162   0.05289   0.04583  -0.0642   0.0098   1.0000
  13.500   1.4129   0.05625   0.04935  -0.0638   0.0093   1.0000
  13.750   1.4114   0.05953   0.05280  -0.0636   0.0089   1.0000
  14.000   1.4084   0.06312   0.05657  -0.0636   0.0085   1.0000
  14.250   1.4046   0.06696   0.06057  -0.0638   0.0083   1.0000
  14.500   1.4003   0.07100   0.06478  -0.0643   0.0080   1.0000
  14.750   1.3956   0.07525   0.06918  -0.0651   0.0078   1.0000
  15.000   1.3901   0.07974   0.07383  -0.0661   0.0076   1.0000
  15.250   1.3842   0.08443   0.07868  -0.0673   0.0075   1.0000
  15.500   1.3780   0.08933   0.08373  -0.0689   0.0073   1.0000
  15.750   1.3710   0.09448   0.08904  -0.0706   0.0072   1.0000
  16.000   1.3638   0.09980   0.09451  -0.0726   0.0071   1.0000
  16.250   1.3560   0.10535   0.10020  -0.0749   0.0070   1.0000
  16.500   1.3482   0.11103   0.10604  -0.0774   0.0069   1.0000
  16.750   1.3403   0.11685   0.11200  -0.0801   0.0068   1.0000
  17.000   1.3323   0.12276   0.11805  -0.0830   0.0067   1.0000
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