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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 100,000
Max Cl/Cd: 43.74 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e559-il-100000.txt
Download as CSV file: xf-e559-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 559 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6327   0.06202   0.05671  -0.0795   1.0000   0.0662
 -11.000  -0.6639   0.05784   0.05248  -0.0799   1.0000   0.0659
 -10.750  -0.6959   0.05465   0.04926  -0.0790   1.0000   0.0656
 -10.500  -0.7212   0.05110   0.04555  -0.0786   1.0000   0.0655
 -10.250  -0.7380   0.04784   0.04205  -0.0778   1.0000   0.0656
 -10.000  -0.7484   0.04472   0.03860  -0.0770   1.0000   0.0661
  -9.750  -0.7485   0.04183   0.03552  -0.0760   1.0000   0.0672
  -9.500  -0.7391   0.04039   0.03419  -0.0746   1.0000   0.0696
  -9.250  -0.7315   0.03860   0.03226  -0.0737   1.0000   0.0717
  -9.000  -0.7224   0.03665   0.03005  -0.0731   1.0000   0.0745
  -8.750  -0.7106   0.03461   0.02760  -0.0728   1.0000   0.0770
  -8.500  -0.6971   0.03304   0.02621  -0.0717   1.0000   0.0803
  -8.250  -0.6822   0.03185   0.02495  -0.0711   1.0000   0.0850
  -8.000  -0.6666   0.03043   0.02342  -0.0707   1.0000   0.0910
  -7.750  -0.6335   0.02903   0.02193  -0.0733   0.9958   0.1023
  -7.500  -0.5898   0.02779   0.02084  -0.0779   0.9881   0.1242
  -7.250  -0.5443   0.02706   0.02010  -0.0827   0.9799   0.1553
  -7.000  -0.4985   0.02710   0.02023  -0.0868   0.9715   0.1808
  -6.750  -0.4568   0.02709   0.02007  -0.0902   0.9613   0.2037
  -6.500  -0.4174   0.02780   0.02098  -0.0923   0.9509   0.2233
  -6.250  -0.3763   0.02829   0.02151  -0.0946   0.9413   0.2417
  -6.000  -0.3322   0.02821   0.02140  -0.0975   0.9330   0.2577
  -5.750  -0.2960   0.02797   0.02107  -0.0992   0.9222   0.2715
  -5.500  -0.2470   0.02770   0.02071  -0.1029   0.9165   0.2870
  -5.250  -0.2131   0.02732   0.02017  -0.1041   0.9047   0.3006
  -5.000  -0.1738   0.02717   0.02003  -0.1058   0.8958   0.3128
  -4.750  -0.1316   0.02684   0.01969  -0.1080   0.8880   0.3246
  -4.500  -0.0914   0.02628   0.01901  -0.1101   0.8794   0.3372
  -4.250  -0.0466   0.02558   0.01814  -0.1131   0.8722   0.3509
  -4.000   0.0077   0.02496   0.01746  -0.1173   0.8685   0.3641
  -3.750   0.0398   0.02461   0.01710  -0.1178   0.8564   0.3735
  -3.500   0.0929   0.02377   0.01611  -0.1221   0.8518   0.3872
  -3.250   0.1246   0.02344   0.01572  -0.1226   0.8390   0.3976
  -3.000   0.1624   0.02298   0.01520  -0.1240   0.8288   0.4079
  -2.750   0.2063   0.02234   0.01438  -0.1268   0.8199   0.4206
  -2.500   0.2368   0.02212   0.01415  -0.1269   0.8070   0.4298
  -2.250   0.2717   0.02175   0.01368  -0.1280   0.7957   0.4406
  -2.000   0.3101   0.02137   0.01310  -0.1297   0.7853   0.4530
  -1.750   0.3362   0.02125   0.01302  -0.1290   0.7719   0.4612
  -1.500   0.3662   0.02107   0.01271  -0.1293   0.7596   0.4726
  -1.250   0.3996   0.02088   0.01244  -0.1300   0.7493   0.4832
  -1.000   0.4262   0.02079   0.01231  -0.1296   0.7367   0.4933
  -0.750   0.4538   0.02076   0.01217  -0.1295   0.7246   0.5054
  -0.500   0.4839   0.02066   0.01205  -0.1295   0.7147   0.5155
  -0.250   0.5105   0.02062   0.01197  -0.1291   0.7030   0.5269
   0.000   0.5371   0.02068   0.01196  -0.1289   0.6918   0.5397
   0.250   0.5683   0.02059   0.01183  -0.1291   0.6831   0.5514
   0.500   0.5908   0.02070   0.01199  -0.1281   0.6714   0.5631
   0.750   0.6186   0.02075   0.01199  -0.1279   0.6618   0.5769
   1.000   0.6461   0.02080   0.01201  -0.1277   0.6522   0.5916
   1.250   0.6703   0.02094   0.01220  -0.1269   0.6425   0.6055
   1.500   0.6987   0.02096   0.01220  -0.1267   0.6341   0.6213
   1.750   0.7214   0.02116   0.01249  -0.1258   0.6244   0.6373
   2.000   0.7507   0.02119   0.01249  -0.1257   0.6168   0.6565
   2.250   0.7722   0.02145   0.01286  -0.1246   0.6074   0.6763
   2.500   0.7995   0.02148   0.01292  -0.1241   0.6002   0.6984
   2.750   0.8196   0.02174   0.01332  -0.1226   0.5914   0.7235
   3.000   0.8449   0.02179   0.01343  -0.1217   0.5843   0.7542
   3.250   0.8633   0.02201   0.01382  -0.1197   0.5768   0.7921
   3.500   0.8788   0.02200   0.01399  -0.1168   0.5697   0.8460
   3.750   0.9086   0.02183   0.01391  -0.1168   0.5630   1.0000
   4.000   0.9385   0.02240   0.01441  -0.1182   0.5544   1.0000
   4.250   0.9745   0.02272   0.01451  -0.1199   0.5486   1.0000
   4.500   0.9937   0.02344   0.01530  -0.1189   0.5402   1.0000
   4.750   1.0247   0.02377   0.01553  -0.1195   0.5338   1.0000
   5.000   1.0474   0.02444   0.01623  -0.1189   0.5269   1.0000
   5.250   1.0720   0.02498   0.01677  -0.1186   0.5200   1.0000
   5.500   1.1061   0.02529   0.01693  -0.1195   0.5148   1.0000
   5.750   1.1194   0.02621   0.01804  -0.1175   0.5067   1.0000
   6.000   1.1489   0.02659   0.01836  -0.1178   0.5009   1.0000
   6.250   1.1706   0.02732   0.01916  -0.1170   0.4945   1.0000
   6.500   1.1911   0.02802   0.01992  -0.1160   0.4875   1.0000
   6.750   1.2252   0.02826   0.02006  -0.1169   0.4823   1.0000
   7.000   1.2359   0.02939   0.02139  -0.1146   0.4749   1.0000
   7.250   1.2625   0.02980   0.02181  -0.1144   0.4686   1.0000
   7.500   1.2886   0.03040   0.02241  -0.1142   0.4630   1.0000
   7.750   1.3007   0.03141   0.02360  -0.1120   0.4555   1.0000
   8.000   1.3349   0.03154   0.02366  -0.1128   0.4500   1.0000
   8.250   1.3438   0.03277   0.02508  -0.1103   0.4428   1.0000
   8.500   1.3675   0.03324   0.02560  -0.1097   0.4362   1.0000
   8.750   1.3966   0.03362   0.02597  -0.1098   0.4303   1.0000
   9.000   1.4020   0.03484   0.02740  -0.1068   0.4226   1.0000
   9.250   1.4424   0.03458   0.02704  -0.1082   0.4166   1.0000
   9.500   1.4408   0.03613   0.02885  -0.1044   0.4089   1.0000
   9.750   1.4721   0.03609   0.02880  -0.1046   0.4020   1.0000
  10.000   1.4828   0.03706   0.02990  -0.1023   0.3947   1.0000
  10.250   1.5031   0.03740   0.03030  -0.1011   0.3870   1.0000
  10.500   1.5245   0.03779   0.03074  -0.1001   0.3797   1.0000
  10.750   1.5349   0.03844   0.03152  -0.0976   0.3716   1.0000
  11.000   1.5608   0.03851   0.03159  -0.0971   0.3639   1.0000
  11.250   1.5654   0.03928   0.03250  -0.0939   0.3557   1.0000
  11.500   1.5882   0.03934   0.03257  -0.0929   0.3475   1.0000
  11.750   1.5895   0.04004   0.03341  -0.0892   0.3394   1.0000
  12.000   1.6054   0.04026   0.03365  -0.0873   0.3312   1.0000
  12.250   1.6074   0.04089   0.03437  -0.0839   0.3229   1.0000
  12.500   1.6135   0.04153   0.03507  -0.0811   0.3146   1.0000
  12.750   1.6289   0.04152   0.03505  -0.0792   0.3053   1.0000
  13.000   1.6138   0.04336   0.03706  -0.0748   0.2978   1.0000
  13.250   1.6420   0.04272   0.03630  -0.0742   0.2872   1.0000
  13.500   1.6078   0.04593   0.03982  -0.0691   0.2806   1.0000
  13.750   1.6236   0.04605   0.03987  -0.0677   0.2704   1.0000
  14.000   1.6024   0.04898   0.04299  -0.0646   0.2624   1.0000
  14.250   1.6009   0.05065   0.04468  -0.0629   0.2531   1.0000
  14.500   1.6134   0.05115   0.04506  -0.0616   0.2419   1.0000
  14.750   1.5790   0.05619   0.05039  -0.0598   0.2348   1.0000
  15.000   1.5810   0.05793   0.05208  -0.0588   0.2245   1.0000
  15.250   1.5682   0.06139   0.05562  -0.0581   0.2152   1.0000
  15.500   1.5522   0.06558   0.05990  -0.0579   0.2065   1.0000
  15.750   1.5540   0.06773   0.06197  -0.0574   0.1960   1.0000
  16.000   1.5346   0.07277   0.06716  -0.0579   0.1876   1.0000
  16.250   1.5256   0.07672   0.07113  -0.0582   0.1787   1.0000
  16.500   1.5306   0.07876   0.07301  -0.0580   0.1683   1.0000
  16.750   1.5054   0.08537   0.07985  -0.0597   0.1615   1.0000
  17.000   1.5065   0.08820   0.08260  -0.0599   0.1525   1.0000
  17.250   1.4939   0.09324   0.08774  -0.0613   0.1451   1.0000
  17.500   1.4877   0.09740   0.09192  -0.0623   0.1377   1.0000
  17.750   1.4858   0.10088   0.09537  -0.0632   0.1300   1.0000
  18.000   1.4733   0.10631   0.10092  -0.0651   0.1241   1.0000
  18.250   1.4717   0.10988   0.10447  -0.0662   0.1172   1.0000
  18.500   1.4629   0.11481   0.10949  -0.0681   0.1118   1.0000
  18.750   1.4476   0.12099   0.11583  -0.0710   0.1071   1.0000
  19.000   1.4569   0.12268   0.11741  -0.0712   0.1003   1.0000
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