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EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 435 AIRFOIL (e435-il)
Reynolds number: 500,000
Max Cl/Cd: 111.77 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e435-il-500000-n5.txt
Download as CSV file: xf-e435-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 435 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2947   0.05501   0.05209  -0.1337   0.9291   0.0056
 -11.750  -0.3014   0.04365   0.04030  -0.1502   0.9160   0.0055
 -11.500  -0.3010   0.03757   0.03382  -0.1588   0.8966   0.0055
 -11.250  -0.3075   0.03375   0.02964  -0.1613   0.8760   0.0055
 -11.000  -0.3112   0.03130   0.02694  -0.1614   0.8602   0.0054
 -10.750  -0.3144   0.02922   0.02461  -0.1605   0.8470   0.0054
 -10.500  -0.3213   0.02696   0.02205  -0.1587   0.8349   0.0055
 -10.250  -0.3206   0.02552   0.02042  -0.1568   0.8255   0.0054
 -10.000  -0.3208   0.02421   0.01889  -0.1544   0.8174   0.0055
  -9.750  -0.3147   0.02306   0.01758  -0.1527   0.8104   0.0054
  -9.500  -0.3041   0.02185   0.01615  -0.1513   0.8041   0.0055
  -9.250  -0.2904   0.02078   0.01490  -0.1501   0.7987   0.0055
  -9.000  -0.2743   0.01987   0.01385  -0.1491   0.7932   0.0055
  -8.750  -0.2568   0.01901   0.01284  -0.1482   0.7885   0.0056
  -8.500  -0.2379   0.01823   0.01191  -0.1475   0.7843   0.0056
  -8.250  -0.2184   0.01747   0.01106  -0.1468   0.7799   0.0057
  -8.000  -0.1977   0.01683   0.01032  -0.1462   0.7755   0.0057
  -7.750  -0.1772   0.01611   0.00949  -0.1456   0.7714   0.0058
  -7.500  -0.1554   0.01548   0.00877  -0.1453   0.7679   0.0059
  -7.250  -0.1330   0.01488   0.00812  -0.1449   0.7643   0.0061
  -7.000  -0.1094   0.01439   0.00757  -0.1447   0.7604   0.0063
  -6.750  -0.0851   0.01396   0.00708  -0.1445   0.7567   0.0065
  -6.500  -0.0600   0.01357   0.00662  -0.1445   0.7534   0.0068
  -6.250  -0.0345   0.01319   0.00617  -0.1445   0.7504   0.0073
  -6.000  -0.0086   0.01284   0.00578  -0.1445   0.7470   0.0077
  -5.750   0.0174   0.01247   0.00537  -0.1446   0.7435   0.0085
  -5.500   0.0440   0.01218   0.00502  -0.1447   0.7402   0.0096
  -5.250   0.0711   0.01190   0.00470  -0.1450   0.7373   0.0113
  -5.000   0.0984   0.01163   0.00441  -0.1452   0.7344   0.0148
  -4.750   0.1257   0.01135   0.00416  -0.1455   0.7311   0.0217
  -4.500   0.1532   0.01108   0.00394  -0.1458   0.7278   0.0338
  -4.250   0.1810   0.01080   0.00373  -0.1463   0.7247   0.0535
  -4.000   0.2091   0.01049   0.00351  -0.1468   0.7217   0.0837
  -3.750   0.2376   0.01015   0.00331  -0.1475   0.7188   0.1306
  -3.500   0.2662   0.00970   0.00312  -0.1483   0.7157   0.2000
  -3.250   0.2954   0.00918   0.00289  -0.1494   0.7124   0.2949
  -3.000   0.3256   0.00853   0.00267  -0.1508   0.7091   0.4289
  -2.750   0.3552   0.00832   0.00268  -0.1515   0.7061   0.5220
  -2.250   0.4130   0.00835   0.00272  -0.1522   0.7001   0.5678
  -2.000   0.4416   0.00838   0.00272  -0.1524   0.6966   0.5795
  -1.750   0.4703   0.00843   0.00272  -0.1527   0.6932   0.5906
  -1.500   0.4987   0.00850   0.00278  -0.1528   0.6899   0.6036
  -1.250   0.5273   0.00859   0.00284  -0.1530   0.6869   0.6150
  -1.000   0.5556   0.00864   0.00287  -0.1532   0.6833   0.6227
  -0.750   0.5840   0.00867   0.00287  -0.1534   0.6795   0.6261
  -0.500   0.6120   0.00869   0.00288  -0.1536   0.6757   0.6284
  -0.250   0.6402   0.00874   0.00288  -0.1538   0.6721   0.6308
   0.000   0.6683   0.00877   0.00290  -0.1539   0.6683   0.6333
   0.250   0.6962   0.00880   0.00292  -0.1541   0.6639   0.6356
   0.500   0.7240   0.00885   0.00293  -0.1542   0.6595   0.6381
   0.750   0.7519   0.00891   0.00294  -0.1544   0.6555   0.6407
   1.000   0.7795   0.00894   0.00299  -0.1545   0.6510   0.6429
   1.250   0.8066   0.00898   0.00303  -0.1545   0.6459   0.6449
   1.500   0.8336   0.00904   0.00308  -0.1544   0.6408   0.6470
   1.750   0.8606   0.00909   0.00314  -0.1544   0.6356   0.6493
   2.000   0.8873   0.00915   0.00320  -0.1544   0.6297   0.6517
   2.250   0.9139   0.00924   0.00325  -0.1542   0.6242   0.6544
   2.500   0.9405   0.00931   0.00333  -0.1542   0.6184   0.6571
   2.750   0.9666   0.00938   0.00341  -0.1540   0.6119   0.6595
   3.000   0.9922   0.00947   0.00349  -0.1537   0.6055   0.6616
   3.250   1.0176   0.00955   0.00360  -0.1534   0.5979   0.6639
   3.500   1.0423   0.00967   0.00371  -0.1529   0.5905   0.6664
   3.750   1.0672   0.00977   0.00382  -0.1525   0.5820   0.6690
   4.000   1.0912   0.00990   0.00394  -0.1519   0.5736   0.6718
   4.250   1.1148   0.01004   0.00408  -0.1513   0.5639   0.6746
   4.500   1.1377   0.01019   0.00423  -0.1505   0.5538   0.6773
   4.750   1.1590   0.01037   0.00440  -0.1494   0.5429   0.6800
   5.000   1.1797   0.01056   0.00459  -0.1482   0.5304   0.6828
   5.250   1.1992   0.01075   0.00477  -0.1467   0.5180   0.6858
   5.500   1.2167   0.01098   0.00498  -0.1449   0.5048   0.6889
   5.750   1.2332   0.01125   0.00523  -0.1429   0.4909   0.6919
   6.000   1.2491   0.01157   0.00552  -0.1408   0.4757   0.6946
   6.250   1.2637   0.01194   0.00586  -0.1385   0.4589   0.6976
   6.500   1.2775   0.01236   0.00624  -0.1362   0.4412   0.7011
   6.750   1.2900   0.01284   0.00667  -0.1336   0.4228   0.7050
   7.000   1.3012   0.01339   0.00716  -0.1309   0.4036   0.7087
   7.500   1.3230   0.01457   0.00827  -0.1257   0.3676   0.7157
   7.750   1.3334   0.01525   0.00890  -0.1231   0.3490   0.7197
   8.000   1.3436   0.01596   0.00957  -0.1207   0.3316   0.7238
   8.250   1.3533   0.01673   0.01031  -0.1182   0.3147   0.7277
   8.500   1.3627   0.01755   0.01111  -0.1158   0.2982   0.7320
   8.750   1.3717   0.01845   0.01197  -0.1134   0.2816   0.7370
   9.000   1.3804   0.01941   0.01289  -0.1111   0.2651   0.7422
   9.250   1.3889   0.02041   0.01387  -0.1089   0.2493   0.7472
   9.500   1.3970   0.02148   0.01493  -0.1067   0.2335   0.7530
   9.750   1.4048   0.02263   0.01605  -0.1046   0.2181   0.7588
  10.000   1.4122   0.02384   0.01724  -0.1026   0.2026   0.7648
  10.250   1.4199   0.02508   0.01846  -0.1007   0.1883   0.7717
  10.500   1.4282   0.02632   0.01970  -0.0989   0.1758   0.7789
  10.750   1.4354   0.02766   0.02104  -0.0971   0.1628   0.7876
  11.000   1.4422   0.02907   0.02246  -0.0954   0.1498   0.7973
  11.500   1.4550   0.03205   0.02546  -0.0921   0.1264   0.8224
  12.000   1.4686   0.03495   0.02848  -0.0889   0.1069   0.8682
  12.250   1.4708   0.03638   0.03003  -0.0867   0.0987   1.0000
  12.500   1.4775   0.03814   0.03177  -0.0856   0.0897   1.0000
  12.750   1.4848   0.03989   0.03352  -0.0845   0.0819   1.0000
  13.000   1.4907   0.04181   0.03543  -0.0835   0.0744   1.0000
  13.250   1.4963   0.04379   0.03741  -0.0826   0.0672   1.0000
  13.500   1.5026   0.04575   0.03940  -0.0817   0.0610   1.0000
  13.750   1.5078   0.04786   0.04152  -0.0809   0.0551   1.0000
  14.000   1.5126   0.05008   0.04375  -0.0802   0.0496   1.0000
  14.250   1.5183   0.05225   0.04596  -0.0796   0.0451   1.0000
  14.500   1.5222   0.05465   0.04838  -0.0790   0.0410   1.0000
  14.750   1.5274   0.05695   0.05074  -0.0785   0.0374   1.0000
  15.000   1.5310   0.05951   0.05333  -0.0781   0.0340   1.0000
  15.250   1.5349   0.06206   0.05594  -0.0778   0.0309   1.0000
  15.500   1.5377   0.06482   0.05874  -0.0775   0.0281   1.0000
  15.750   1.5409   0.06756   0.06154  -0.0774   0.0256   1.0000
  16.000   1.5422   0.07059   0.06462  -0.0773   0.0230   1.0000
  16.250   1.5444   0.07357   0.06767  -0.0774   0.0211   1.0000
  16.500   1.5457   0.07673   0.07090  -0.0776   0.0193   1.0000
  16.750   1.5461   0.08006   0.07429  -0.0778   0.0173   1.0000
  17.000   1.5463   0.08348   0.07778  -0.0782   0.0156   1.0000
  17.250   1.5464   0.08696   0.08133  -0.0787   0.0143   1.0000
  17.500   1.5454   0.09065   0.08511  -0.0794   0.0130   1.0000
  17.750   1.5445   0.09440   0.08894  -0.0801   0.0118   1.0000
  18.000   1.5422   0.09841   0.09302  -0.0811   0.0108   1.0000
  18.250   1.5414   0.10221   0.09693  -0.0820   0.0099   1.0000
  18.500   1.5392   0.10626   0.10107  -0.0832   0.0092   1.0000
  18.750   1.5359   0.11056   0.10545  -0.0845   0.0086   1.0000
  19.000   1.5338   0.11469   0.10970  -0.0859   0.0081   1.0000
  19.250   1.5309   0.11898   0.11409  -0.0875   0.0075   1.0000
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