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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 100,000
Max Cl/Cd: 55.33 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e562-il-100000-n5.txt
Download as CSV file: xf-e562-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 562 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4934   0.10323   0.09775  -0.0524   1.0000   0.0295
 -12.750  -0.5325   0.09127   0.08570  -0.0587   1.0000   0.0292
 -12.500  -0.5623   0.08255   0.07688  -0.0634   1.0000   0.0288
 -12.250  -0.5868   0.07550   0.06972  -0.0670   1.0000   0.0286
 -12.000  -0.6095   0.06931   0.06340  -0.0702   1.0000   0.0285
 -11.750  -0.6298   0.06398   0.05793  -0.0727   1.0000   0.0287
 -11.500  -0.6460   0.05963   0.05346  -0.0742   1.0000   0.0288
 -11.250  -0.6620   0.05571   0.04941  -0.0750   1.0000   0.0289
 -11.000  -0.6776   0.05231   0.04589  -0.0752   1.0000   0.0291
 -10.750  -0.6949   0.04939   0.04285  -0.0746   1.0000   0.0294
 -10.500  -0.7145   0.04694   0.04030  -0.0729   1.0000   0.0296
 -10.250  -0.7233   0.04461   0.03794  -0.0721   1.0000   0.0300
 -10.000  -0.7257   0.04260   0.03590  -0.0712   1.0000   0.0305
  -9.750  -0.7250   0.04079   0.03405  -0.0701   1.0000   0.0312
  -9.500  -0.7217   0.03902   0.03220  -0.0691   1.0000   0.0320
  -9.250  -0.7158   0.03734   0.03041  -0.0681   1.0000   0.0330
  -9.000  -0.6932   0.03551   0.02836  -0.0699   0.9968   0.0347
  -8.750  -0.6628   0.03369   0.02643  -0.0731   0.9916   0.0371
  -8.500  -0.6313   0.03212   0.02478  -0.0762   0.9860   0.0399
  -8.250  -0.5997   0.03066   0.02310  -0.0786   0.9804   0.0430
  -8.000  -0.5681   0.02910   0.02153  -0.0817   0.9743   0.0471
  -7.750  -0.5370   0.02776   0.02004  -0.0839   0.9678   0.0521
  -7.500  -0.5033   0.02629   0.01852  -0.0869   0.9619   0.0590
  -7.250  -0.4728   0.02490   0.01710  -0.0891   0.9544   0.0694
  -7.000  -0.4368   0.02353   0.01572  -0.0922   0.9489   0.0866
  -6.750  -0.4060   0.02237   0.01459  -0.0941   0.9409   0.1119
  -6.500  -0.3690   0.02135   0.01367  -0.0970   0.9355   0.1442
  -6.250  -0.3374   0.02069   0.01304  -0.0985   0.9271   0.1762
  -6.000  -0.2999   0.02019   0.01255  -0.1009   0.9213   0.2122
  -5.750  -0.2679   0.01988   0.01223  -0.1020   0.9127   0.2386
  -5.500  -0.2305   0.01955   0.01177  -0.1040   0.9066   0.2603
  -5.250  -0.1980   0.01929   0.01142  -0.1049   0.8981   0.2777
  -5.000  -0.1614   0.01901   0.01105  -0.1065   0.8915   0.2941
  -4.750  -0.1281   0.01876   0.01069  -0.1075   0.8830   0.3083
  -4.500  -0.0915   0.01849   0.01037  -0.1089   0.8758   0.3207
  -4.250  -0.0577   0.01826   0.01007  -0.1099   0.8668   0.3324
  -4.000  -0.0192   0.01799   0.00969  -0.1118   0.8594   0.3453
  -3.750   0.0153   0.01780   0.00938  -0.1130   0.8493   0.3583
  -3.500   0.0565   0.01756   0.00907  -0.1153   0.8419   0.3705
  -3.250   0.0895   0.01739   0.00884  -0.1161   0.8303   0.3800
  -3.000   0.1266   0.01717   0.00850  -0.1178   0.8200   0.3911
  -2.750   0.1645   0.01698   0.00824  -0.1195   0.8099   0.4008
  -2.500   0.1975   0.01684   0.00802  -0.1203   0.7971   0.4103
  -2.250   0.2316   0.01673   0.00780  -0.1213   0.7849   0.4207
  -2.000   0.2660   0.01661   0.00763  -0.1224   0.7730   0.4298
  -1.750   0.3005   0.01652   0.00741  -0.1235   0.7608   0.4406
  -1.500   0.3306   0.01648   0.00734  -0.1238   0.7474   0.4493
  -1.250   0.3612   0.01645   0.00723  -0.1242   0.7343   0.4593
  -1.000   0.3916   0.01643   0.00714  -0.1245   0.7217   0.4690
  -0.750   0.4221   0.01642   0.00707  -0.1249   0.7096   0.4785
  -0.500   0.4514   0.01644   0.00700  -0.1250   0.6969   0.4893
  -0.250   0.4788   0.01646   0.00703  -0.1248   0.6843   0.4981
   0.000   0.5071   0.01651   0.00701  -0.1247   0.6722   0.5086
   0.250   0.5355   0.01655   0.00701  -0.1247   0.6610   0.5188
   0.500   0.5625   0.01661   0.00705  -0.1244   0.6491   0.5288
   0.750   0.5896   0.01669   0.00710  -0.1241   0.6374   0.5402
   1.000   0.6168   0.01677   0.00717  -0.1239   0.6268   0.5507
   1.250   0.6436   0.01686   0.00725  -0.1235   0.6160   0.5619
   1.500   0.6698   0.01697   0.00736  -0.1231   0.6049   0.5742
   1.750   0.6966   0.01708   0.00746  -0.1228   0.5951   0.5866
   2.000   0.7223   0.01719   0.00760  -0.1223   0.5847   0.5993
   2.250   0.7482   0.01732   0.00775  -0.1218   0.5746   0.6130
   2.500   0.7749   0.01745   0.00788  -0.1215   0.5656   0.6278
   2.750   0.7997   0.01759   0.00809  -0.1208   0.5554   0.6439
   3.000   0.8255   0.01774   0.00825  -0.1203   0.5466   0.6614
   3.250   0.8499   0.01788   0.00849  -0.1195   0.5371   0.6808
   3.500   0.8746   0.01804   0.00870  -0.1188   0.5284   0.7033
   3.750   0.8980   0.01817   0.00892  -0.1178   0.5196   0.7282
   4.000   0.9204   0.01831   0.00917  -0.1165   0.5112   0.7589
   4.250   0.9411   0.01840   0.00937  -0.1149   0.5030   0.7977
   4.500   0.9586   0.01845   0.00957  -0.1125   0.4949   0.8545
   4.750   0.9829   0.01847   0.00968  -0.1116   0.4868   1.0000
   5.000   1.0093   0.01881   0.00999  -0.1116   0.4781   1.0000
   5.250   1.0358   0.01914   0.01027  -0.1115   0.4701   1.0000
   5.500   1.0609   0.01950   0.01065  -0.1111   0.4618   1.0000
   5.750   1.0865   0.01984   0.01097  -0.1109   0.4539   1.0000
   6.000   1.1107   0.02023   0.01139  -0.1103   0.4457   1.0000
   6.250   1.1356   0.02059   0.01174  -0.1099   0.4380   1.0000
   6.500   1.1589   0.02099   0.01221  -0.1092   0.4298   1.0000
   6.750   1.1829   0.02138   0.01259  -0.1086   0.4221   1.0000
   7.000   1.2052   0.02180   0.01309  -0.1078   0.4138   1.0000
   7.250   1.2283   0.02220   0.01351  -0.1071   0.4060   1.0000
   7.500   1.2495   0.02265   0.01404  -0.1060   0.3975   1.0000
   7.750   1.2716   0.02307   0.01447  -0.1051   0.3896   1.0000
   8.000   1.2910   0.02355   0.01506  -0.1038   0.3806   1.0000
   8.250   1.3122   0.02398   0.01549  -0.1028   0.3727   1.0000
   8.500   1.3292   0.02449   0.01614  -0.1011   0.3631   1.0000
   8.750   1.3480   0.02497   0.01664  -0.0997   0.3547   1.0000
   9.000   1.3637   0.02549   0.01728  -0.0978   0.3451   1.0000
   9.250   1.3786   0.02602   0.01789  -0.0958   0.3361   1.0000
   9.500   1.3921   0.02656   0.01847  -0.0936   0.3269   1.0000
   9.750   1.4037   0.02719   0.01923  -0.0912   0.3170   1.0000
  10.000   1.4153   0.02783   0.01990  -0.0888   0.3076   1.0000
  10.250   1.4248   0.02856   0.02072  -0.0863   0.2974   1.0000
  10.500   1.4337   0.02937   0.02165  -0.0838   0.2871   1.0000
  10.750   1.4415   0.03024   0.02255  -0.0812   0.2773   1.0000
  11.000   1.4476   0.03124   0.02365  -0.0787   0.2665   1.0000
  11.250   1.4528   0.03236   0.02488  -0.0762   0.2557   1.0000
  11.500   1.4566   0.03363   0.02620  -0.0737   0.2451   1.0000
  11.750   1.4586   0.03507   0.02767  -0.0714   0.2345   1.0000
  12.000   1.4599   0.03671   0.02944  -0.0692   0.2231   1.0000
  12.250   1.4598   0.03854   0.03135  -0.0672   0.2122   1.0000
  12.500   1.4577   0.04066   0.03351  -0.0654   0.2015   1.0000
  12.750   1.4540   0.04306   0.03595  -0.0638   0.1907   1.0000
  13.000   1.4503   0.04567   0.03866  -0.0625   0.1797   1.0000
  13.250   1.4447   0.04861   0.04166  -0.0615   0.1695   1.0000
  13.500   1.4372   0.05190   0.04498  -0.0608   0.1601   1.0000
  13.750   1.4298   0.05542   0.04858  -0.0605   0.1504   1.0000
  14.000   1.4217   0.05919   0.05243  -0.0604   0.1416   1.0000
  14.250   1.4111   0.06342   0.05668  -0.0607   0.1339   1.0000
  14.500   1.4031   0.06761   0.06099  -0.0612   0.1257   1.0000
  14.750   1.3924   0.07224   0.06564  -0.0620   0.1189   1.0000
  15.000   1.3834   0.07688   0.07041  -0.0630   0.1118   1.0000
  15.250   1.3728   0.08182   0.07539  -0.0642   0.1059   1.0000
  15.500   1.3642   0.08668   0.08037  -0.0656   0.0995   1.0000
  15.750   1.3534   0.09193   0.08561  -0.0672   0.0945   1.0000
  16.000   1.3463   0.09682   0.09066  -0.0688   0.0886   1.0000
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