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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 200,000
Max Cl/Cd: 70.36 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e559-il-200000.txt
Download as CSV file: xf-e559-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6202   0.08428   0.07999  -0.0691   1.0000   0.0351
 -13.750  -0.6462   0.07710   0.07270  -0.0730   1.0000   0.0347
 -13.500  -0.6725   0.07039   0.06585  -0.0770   1.0000   0.0346
 -13.250  -0.6953   0.06465   0.05996  -0.0804   1.0000   0.0346
 -13.000  -0.7174   0.05939   0.05454  -0.0832   1.0000   0.0346
 -12.750  -0.7362   0.05494   0.04995  -0.0853   1.0000   0.0347
 -12.500  -0.7534   0.05110   0.04597  -0.0865   1.0000   0.0348
 -12.250  -0.7716   0.04776   0.04249  -0.0871   1.0000   0.0349
 -12.000  -0.7878   0.04513   0.03976  -0.0863   1.0000   0.0349
 -11.750  -0.8114   0.04303   0.03757  -0.0841   1.0000   0.0350
 -11.500  -0.8254   0.04087   0.03523  -0.0831   1.0000   0.0352
 -11.250  -0.8260   0.03857   0.03293  -0.0811   1.0000   0.0359
 -11.000  -0.8240   0.03699   0.03135  -0.0794   1.0000   0.0365
 -10.750  -0.8207   0.03554   0.02987  -0.0777   1.0000   0.0372
 -10.500  -0.8160   0.03414   0.02838  -0.0763   1.0000   0.0380
 -10.250  -0.8093   0.03277   0.02691  -0.0749   1.0000   0.0388
 -10.000  -0.7916   0.03131   0.02531  -0.0753   0.9986   0.0399
  -9.750  -0.7535   0.02960   0.02339  -0.0794   0.9939   0.0420
  -9.500  -0.7187   0.02807   0.02193  -0.0825   0.9883   0.0443
  -9.250  -0.6792   0.02677   0.02053  -0.0862   0.9836   0.0469
  -9.000  -0.6451   0.02527   0.01894  -0.0888   0.9770   0.0498
  -8.750  -0.6055   0.02395   0.01764  -0.0926   0.9722   0.0542
  -8.500  -0.5718   0.02255   0.01621  -0.0952   0.9649   0.0597
  -8.250  -0.5314   0.02107   0.01473  -0.0990   0.9602   0.0698
  -8.000  -0.4976   0.01958   0.01332  -0.1016   0.9524   0.0914
  -7.750  -0.4565   0.01846   0.01229  -0.1052   0.9476   0.1230
  -7.500  -0.4210   0.01784   0.01164  -0.1071   0.9400   0.1444
  -7.250  -0.3801   0.01732   0.01112  -0.1099   0.9345   0.1638
  -7.000  -0.3398   0.01691   0.01066  -0.1124   0.9292   0.1813
  -6.750  -0.3031   0.01653   0.01024  -0.1142   0.9215   0.1965
  -6.500  -0.2593   0.01620   0.00985  -0.1172   0.9178   0.2138
  -6.250  -0.2241   0.01598   0.00960  -0.1184   0.9092   0.2289
  -6.000  -0.1810   0.01569   0.00927  -0.1212   0.9040   0.2434
  -5.750  -0.1374   0.01535   0.00889  -0.1241   0.8980   0.2561
  -5.500  -0.0971   0.01505   0.00847  -0.1263   0.8888   0.2681
  -5.250  -0.0551   0.01481   0.00820  -0.1288   0.8800   0.2795
  -5.000  -0.0129   0.01453   0.00788  -0.1314   0.8699   0.2899
  -4.750   0.0236   0.01434   0.00754  -0.1329   0.8564   0.3005
  -4.500   0.0591   0.01420   0.00739  -0.1342   0.8426   0.3094
  -4.250   0.0934   0.01405   0.00710  -0.1352   0.8285   0.3188
  -4.000   0.1257   0.01399   0.00697  -0.1358   0.8141   0.3273
  -3.750   0.1569   0.01390   0.00674  -0.1362   0.7998   0.3360
  -3.500   0.1860   0.01389   0.00665  -0.1362   0.7852   0.3442
  -3.250   0.2136   0.01383   0.00648  -0.1360   0.7705   0.3525
  -3.000   0.2411   0.01382   0.00643  -0.1357   0.7562   0.3603
  -2.750   0.2690   0.01379   0.00626  -0.1355   0.7427   0.3688
  -2.500   0.2969   0.01379   0.00622  -0.1353   0.7301   0.3765
  -2.250   0.3250   0.01380   0.00606  -0.1352   0.7176   0.3852
  -2.000   0.3510   0.01377   0.00605  -0.1346   0.7044   0.3927
  -1.750   0.3785   0.01381   0.00595  -0.1344   0.6923   0.4018
  -1.500   0.4060   0.01380   0.00592  -0.1341   0.6813   0.4093
  -1.000   0.4593   0.01383   0.00586  -0.1334   0.6578   0.4265
  -0.500   0.5134   0.01389   0.00582  -0.1328   0.6366   0.4442
  -0.250   0.5406   0.01396   0.00581  -0.1325   0.6264   0.4543
   0.000   0.5678   0.01399   0.00582  -0.1323   0.6168   0.4631
   0.250   0.5942   0.01404   0.00586  -0.1319   0.6066   0.4731
   0.500   0.6221   0.01413   0.00589  -0.1318   0.5980   0.4835
   0.750   0.6478   0.01416   0.00596  -0.1313   0.5879   0.4935
   1.000   0.6755   0.01428   0.00600  -0.1311   0.5795   0.5054
   1.250   0.7014   0.01431   0.00611  -0.1307   0.5704   0.5164
   1.500   0.7288   0.01442   0.00619  -0.1305   0.5626   0.5285
   1.750   0.7549   0.01449   0.00630  -0.1301   0.5538   0.5418
   2.000   0.7824   0.01463   0.00640  -0.1299   0.5464   0.5565
   2.250   0.8080   0.01469   0.00656  -0.1294   0.5381   0.5714
   2.750   0.8608   0.01490   0.00688  -0.1287   0.5233   0.6073
   3.000   0.8876   0.01500   0.00702  -0.1284   0.5166   0.6287
   3.250   0.9128   0.01511   0.00726  -0.1279   0.5095   0.6538
   3.500   0.9379   0.01519   0.00745  -0.1272   0.5028   0.6847
   3.750   0.9634   0.01531   0.00767  -0.1266   0.4968   0.7249
   4.000   0.9839   0.01532   0.00791  -0.1249   0.4898   0.7779
   4.250   1.0005   0.01524   0.00801  -0.1221   0.4843   0.8640
   4.500   1.0276   0.01531   0.00814  -0.1218   0.4784   1.0000
   4.750   1.0545   0.01556   0.00838  -0.1217   0.4717   1.0000
   5.000   1.0835   0.01587   0.00856  -0.1221   0.4660   1.0000
   5.250   1.1088   0.01617   0.00890  -0.1217   0.4597   1.0000
   5.500   1.1352   0.01644   0.00916  -0.1215   0.4537   1.0000
   5.750   1.1644   0.01682   0.00941  -0.1218   0.4484   1.0000
   6.000   1.1871   0.01709   0.00979  -0.1209   0.4420   1.0000
   6.250   1.2132   0.01737   0.01006  -0.1207   0.4363   1.0000
   6.500   1.2408   0.01776   0.01038  -0.1207   0.4309   1.0000
   6.750   1.2631   0.01805   0.01078  -0.1198   0.4246   1.0000
   7.000   1.2890   0.01835   0.01105  -0.1194   0.4190   1.0000
   7.250   1.3148   0.01874   0.01144  -0.1192   0.4136   1.0000
   7.500   1.3365   0.01905   0.01185  -0.1181   0.4073   1.0000
   7.750   1.3622   0.01936   0.01213  -0.1178   0.4018   1.0000
   8.000   1.3854   0.01976   0.01258  -0.1171   0.3960   1.0000
   8.250   1.4067   0.02007   0.01297  -0.1160   0.3897   1.0000
   8.500   1.4328   0.02041   0.01325  -0.1158   0.3840   1.0000
   8.750   1.4514   0.02079   0.01376  -0.1142   0.3777   1.0000
   9.000   1.4726   0.02108   0.01408  -0.1131   0.3712   1.0000
   9.250   1.4956   0.02147   0.01447  -0.1124   0.3651   1.0000
   9.500   1.5115   0.02180   0.01493  -0.1104   0.3582   1.0000
   9.750   1.5339   0.02212   0.01520  -0.1095   0.3519   1.0000
  10.000   1.5477   0.02252   0.01576  -0.1072   0.3449   1.0000
  10.250   1.5642   0.02283   0.01610  -0.1054   0.3381   1.0000
  10.500   1.5794   0.02325   0.01658  -0.1034   0.3313   1.0000
  10.750   1.5886   0.02361   0.01703  -0.1003   0.3242   1.0000
  11.000   1.6030   0.02404   0.01745  -0.0982   0.3174   1.0000
  11.250   1.6082   0.02453   0.01810  -0.0947   0.3099   1.0000
  11.500   1.6213   0.02503   0.01854  -0.0925   0.3028   1.0000
  11.750   1.6238   0.02569   0.01940  -0.0889   0.2949   1.0000
  12.000   1.6332   0.02634   0.01999  -0.0865   0.2874   1.0000
  12.250   1.6346   0.02721   0.02106  -0.0831   0.2790   1.0000
  12.500   1.6399   0.02813   0.02196  -0.0805   0.2709   1.0000
  12.750   1.6410   0.02926   0.02323  -0.0776   0.2618   1.0000
  13.000   1.6429   0.03053   0.02456  -0.0752   0.2531   1.0000
  13.250   1.6427   0.03202   0.02608  -0.0727   0.2438   1.0000
  13.500   1.6420   0.03372   0.02789  -0.0706   0.2339   1.0000
  13.750   1.6393   0.03569   0.02988  -0.0686   0.2246   1.0000
  14.000   1.6351   0.03795   0.03219  -0.0668   0.2144   1.0000
  14.250   1.6304   0.04045   0.03477  -0.0654   0.2041   1.0000
  14.500   1.6234   0.04332   0.03766  -0.0642   0.1944   1.0000
  14.750   1.6145   0.04657   0.04091  -0.0632   0.1845   1.0000
  15.000   1.6066   0.04995   0.04437  -0.0626   0.1746   1.0000
  15.250   1.5963   0.05374   0.04819  -0.0623   0.1656   1.0000
  15.500   1.5849   0.05785   0.05230  -0.0623   0.1568   1.0000
  15.750   1.5751   0.06199   0.05653  -0.0625   0.1479   1.0000
  16.000   1.5623   0.06660   0.06111  -0.0630   0.1404   1.0000
  16.250   1.5523   0.07111   0.06571  -0.0637   0.1322   1.0000
  16.500   1.5408   0.07590   0.07051  -0.0646   0.1252   1.0000
  16.750   1.5297   0.08082   0.07548  -0.0657   0.1179   1.0000
  17.000   1.5196   0.08568   0.08038  -0.0669   0.1115   1.0000
  17.250   1.5092   0.09072   0.08546  -0.0684   0.1051   1.0000
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