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EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 557 AIRFOIL (e557-il)
Reynolds number: 50,000
Max Cl/Cd: 32.35 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e557-il-50000-n5.txt
Download as CSV file: xf-e557-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 557 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4661   0.09786   0.09046  -0.0633   1.0000   0.0454
 -11.750  -0.4862   0.09105   0.08364  -0.0664   1.0000   0.0451
 -11.500  -0.5083   0.08468   0.07723  -0.0691   1.0000   0.0449
 -11.250  -0.5294   0.07917   0.07167  -0.0712   1.0000   0.0446
 -11.000  -0.5506   0.07428   0.06671  -0.0727   1.0000   0.0445
 -10.750  -0.5730   0.06984   0.06221  -0.0735   1.0000   0.0445
 -10.500  -0.5924   0.06626   0.05854  -0.0733   1.0000   0.0444
 -10.250  -0.6126   0.06318   0.05537  -0.0723   1.0000   0.0445
 -10.000  -0.6332   0.06062   0.05272  -0.0704   1.0000   0.0446
  -9.750  -0.6536   0.05831   0.05030  -0.0682   1.0000   0.0448
  -9.500  -0.6679   0.05566   0.04745  -0.0668   1.0000   0.0452
  -9.250  -0.6699   0.05373   0.04552  -0.0650   1.0000   0.0464
  -9.000  -0.6704   0.05200   0.04376  -0.0632   1.0000   0.0479
  -8.750  -0.6703   0.05016   0.04180  -0.0616   1.0000   0.0498
  -8.500  -0.6677   0.04818   0.03958  -0.0599   1.0000   0.0520
  -8.250  -0.6611   0.04638   0.03759  -0.0579   1.0000   0.0543
  -8.000  -0.6536   0.04513   0.03639  -0.0560   1.0000   0.0572
  -7.750  -0.6451   0.04381   0.03492  -0.0541   1.0000   0.0610
  -7.500  -0.6276   0.04250   0.03357  -0.0533   0.9977   0.0659
  -7.250  -0.5984   0.04112   0.03197  -0.0548   0.9916   0.0744
  -7.000  -0.5715   0.03967   0.03058  -0.0565   0.9850   0.0838
  -6.750  -0.5459   0.03802   0.02895  -0.0585   0.9777   0.0962
  -6.500  -0.5180   0.03618   0.02712  -0.0613   0.9706   0.1143
  -6.250  -0.4896   0.03380   0.02491  -0.0654   0.9631   0.1430
  -6.000  -0.4589   0.03089   0.02264  -0.0709   0.9561   0.2058
  -5.750  -0.4268   0.03122   0.02387  -0.0719   0.9488   0.3289
  -5.500  -0.3947   0.03218   0.02456  -0.0725   0.9401   0.3843
  -5.250  -0.3582   0.03337   0.02547  -0.0733   0.9332   0.4178
  -5.000  -0.3310   0.03398   0.02582  -0.0731   0.9238   0.4416
  -4.750  -0.2984   0.03511   0.02678  -0.0724   0.9174   0.4604
  -4.500  -0.2756   0.03575   0.02728  -0.0708   0.9077   0.4767
  -4.250  -0.2425   0.03627   0.02762  -0.0709   0.9015   0.4930
  -4.000  -0.2195   0.03645   0.02764  -0.0698   0.8919   0.5044
  -3.500  -0.1574   0.03580   0.02657  -0.0723   0.8765   0.5230
  -3.250  -0.1213   0.03548   0.02607  -0.0739   0.8710   0.5287
  -3.000  -0.0973   0.03520   0.02565  -0.0739   0.8612   0.5347
  -2.750  -0.0554   0.03444   0.02463  -0.0779   0.8556   0.5423
  -2.500  -0.0324   0.03431   0.02440  -0.0773   0.8460   0.5463
  -2.250   0.0049   0.03386   0.02378  -0.0796   0.8400   0.5520
  -2.000   0.0372   0.03337   0.02309  -0.0820   0.8313   0.5585
  -1.750   0.0699   0.03310   0.02273  -0.0828   0.8246   0.5623
  -1.500   0.0990   0.03288   0.02243  -0.0835   0.8164   0.5671
  -1.250   0.1359   0.03246   0.02183  -0.0861   0.8092   0.5733
  -1.000   0.1711   0.03214   0.02143  -0.0877   0.8028   0.5776
  -0.750   0.1970   0.03206   0.02130  -0.0877   0.7935   0.5820
  -0.500   0.2410   0.03158   0.02070  -0.0909   0.7890   0.5881
  -0.250   0.2632   0.03161   0.02067  -0.0908   0.7779   0.5929
   0.000   0.3033   0.03125   0.02026  -0.0927   0.7730   0.5974
   0.250   0.3243   0.03137   0.02036  -0.0922   0.7619   0.6026
   0.500   0.3692   0.03095   0.01985  -0.0955   0.7569   0.6091
   0.750   0.3877   0.03115   0.02007  -0.0943   0.7458   0.6131
   1.000   0.4293   0.03079   0.01968  -0.0966   0.7406   0.6189
   1.250   0.4529   0.03100   0.01986  -0.0967   0.7296   0.6252
   1.500   0.4911   0.03067   0.01955  -0.0981   0.7241   0.6303
   1.750   0.5114   0.03098   0.01987  -0.0974   0.7130   0.6361
   2.000   0.5540   0.03061   0.01949  -0.0998   0.7075   0.6429
   2.250   0.5710   0.03100   0.01994  -0.0984   0.6962   0.6481
   2.500   0.6137   0.03064   0.01956  -0.1008   0.6908   0.6558
   3.000   0.6682   0.03085   0.01988  -0.1008   0.6731   0.6689
   3.250   0.6886   0.03126   0.02035  -0.1001   0.6620   0.6761
   3.500   0.7161   0.03135   0.02051  -0.1000   0.6537   0.6833
   3.750   0.7453   0.03146   0.02069  -0.1005   0.6447   0.6919
   4.000   0.7668   0.03177   0.02110  -0.0995   0.6351   0.6994
   4.250   0.8007   0.03168   0.02110  -0.1004   0.6272   0.7089
   4.500   0.8178   0.03217   0.02170  -0.0990   0.6166   0.7176
   4.750   0.8551   0.03189   0.02150  -0.1000   0.6096   0.7281
   5.000   0.8697   0.03254   0.02227  -0.0984   0.5980   0.7386
   5.250   0.9006   0.03242   0.02228  -0.0985   0.5901   0.7501
   5.500   0.9195   0.03279   0.02280  -0.0972   0.5794   0.7624
   5.750   0.9380   0.03320   0.02335  -0.0958   0.5691   0.7761
   6.000   0.9708   0.03290   0.02318  -0.0960   0.5607   0.7924
   6.250   0.9800   0.03356   0.02403  -0.0934   0.5490   0.8095
   6.500   1.0019   0.03357   0.02420  -0.0920   0.5394   0.8318
   6.750   1.0209   0.03354   0.02436  -0.0901   0.5294   0.8620
   7.000   1.0255   0.03398   0.02500  -0.0866   0.5180   0.9286
   7.250   1.0588   0.03410   0.02518  -0.0879   0.5067   1.0000
   7.500   1.0961   0.03411   0.02523  -0.0894   0.4953   1.0000
   7.750   1.1096   0.03502   0.02622  -0.0880   0.4822   1.0000
   8.000   1.1276   0.03573   0.02700  -0.0871   0.4694   1.0000
   8.250   1.1503   0.03617   0.02749  -0.0865   0.4569   1.0000
   8.500   1.1766   0.03638   0.02775  -0.0861   0.4442   1.0000
   8.750   1.1945   0.03693   0.02837  -0.0849   0.4308   1.0000
   9.000   1.2030   0.03799   0.02951  -0.0827   0.4170   1.0000
   9.250   1.2130   0.03896   0.03057  -0.0808   0.4030   1.0000
   9.500   1.2239   0.03992   0.03162  -0.0790   0.3889   1.0000
   9.750   1.2346   0.04088   0.03265  -0.0772   0.3747   1.0000
  10.000   1.2446   0.04192   0.03374  -0.0754   0.3602   1.0000
  10.250   1.2535   0.04305   0.03493  -0.0737   0.3456   1.0000
  10.500   1.2612   0.04431   0.03624  -0.0719   0.3310   1.0000
  10.750   1.2678   0.04571   0.03769  -0.0703   0.3163   1.0000
  11.000   1.2734   0.04724   0.03925  -0.0687   0.3017   1.0000
  11.250   1.2761   0.04911   0.04119  -0.0671   0.2873   1.0000
  11.500   1.2762   0.05134   0.04349  -0.0657   0.2732   1.0000
  11.750   1.2766   0.05367   0.04589  -0.0646   0.2596   1.0000
  12.000   1.2770   0.05609   0.04837  -0.0636   0.2463   1.0000
  12.250   1.2779   0.05856   0.05090  -0.0627   0.2335   1.0000
  12.500   1.2799   0.06098   0.05333  -0.0619   0.2214   1.0000
  12.750   1.2830   0.06328   0.05559  -0.0612   0.2096   1.0000
  13.000   1.2786   0.06673   0.05919  -0.0610   0.1985   1.0000
  13.250   1.2766   0.06998   0.06251  -0.0608   0.1881   1.0000
  13.500   1.2787   0.07266   0.06517  -0.0606   0.1781   1.0000
  13.750   1.2748   0.07637   0.06901  -0.0608   0.1687   1.0000
  14.000   1.2719   0.08004   0.07278  -0.0612   0.1601   1.0000
  14.250   1.2750   0.08278   0.07551  -0.0612   0.1515   1.0000
  14.500   1.2659   0.08770   0.08066  -0.0623   0.1442   1.0000
  14.750   1.2720   0.09002   0.08287  -0.0623   0.1363   1.0000
  15.000   1.2586   0.09596   0.08913  -0.0642   0.1303   1.0000
  15.250   1.2646   0.09835   0.09146  -0.0645   0.1232   1.0000
  15.500   1.2501   0.10477   0.09815  -0.0669   0.1182   1.0000
  15.750   1.2443   0.10961   0.10313  -0.0687   0.1128   1.0000
  16.000   1.2454   0.11317   0.10671  -0.0699   0.1075   1.0000
  16.250   1.2228   0.12172   0.11557  -0.0742   0.1040   1.0000
  16.500   1.2123   0.12793   0.12192  -0.0773   0.0999   1.0000
  16.750   1.2198   0.13028   0.12424  -0.0780   0.0952   1.0000
  17.000   1.1756   0.14485   0.13911  -0.0869   0.0939   1.0000
  17.250   1.0998   0.17045   0.16471  -0.1030   0.0919   1.0000
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