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EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 557 AIRFOIL (e557-il)
Reynolds number: 500,000
Max Cl/Cd: 95.15 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e557-il-500000-n5.txt
Download as CSV file: xf-e557-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.6669   0.12152   0.11840  -0.0454   1.0000   0.0047
 -16.750  -0.6883   0.11305   0.10980  -0.0494   1.0000   0.0046
 -16.500  -0.7088   0.10502   0.10164  -0.0532   1.0000   0.0047
 -16.250  -0.7265   0.09790   0.09440  -0.0565   1.0000   0.0046
 -16.000  -0.7411   0.09152   0.08790  -0.0595   1.0000   0.0046
 -15.750  -0.7537   0.08578   0.08205  -0.0622   1.0000   0.0046
 -15.500  -0.7651   0.08046   0.07663  -0.0646   1.0000   0.0046
 -15.250  -0.7755   0.07550   0.07157  -0.0667   1.0000   0.0047
 -15.000  -0.7825   0.07126   0.06723  -0.0684   1.0000   0.0047
 -14.750  -0.7894   0.06721   0.06309  -0.0699   1.0000   0.0048
 -14.500  -0.7959   0.06340   0.05919  -0.0712   1.0000   0.0049
 -14.250  -0.8030   0.05975   0.05544  -0.0722   1.0000   0.0048
 -14.000  -0.8077   0.05653   0.05214  -0.0729   1.0000   0.0049
 -13.750  -0.8120   0.05357   0.04910  -0.0734   1.0000   0.0050
 -13.500  -0.8188   0.05061   0.04607  -0.0735   1.0000   0.0050
 -13.250  -0.8230   0.04816   0.04355  -0.0733   1.0000   0.0050
 -13.000  -0.8302   0.04560   0.04093  -0.0728   1.0000   0.0051
 -12.750  -0.8299   0.04310   0.03835  -0.0736   0.9994   0.0051
 -12.500  -0.8159   0.04045   0.03559  -0.0769   0.9973   0.0053
 -12.250  -0.8010   0.03788   0.03293  -0.0804   0.9947   0.0053
 -12.000  -0.7860   0.03557   0.03053  -0.0833   0.9919   0.0054
 -11.750  -0.7727   0.03310   0.02797  -0.0862   0.9876   0.0056
 -11.500  -0.7554   0.03074   0.02553  -0.0898   0.9840   0.0057
 -11.250  -0.7451   0.02884   0.02358  -0.0909   0.9766   0.0060
 -11.000  -0.7333   0.02696   0.02163  -0.0924   0.9691   0.0060
 -10.750  -0.7143   0.02502   0.01961  -0.0951   0.9627   0.0063
 -10.500  -0.6934   0.02330   0.01781  -0.0976   0.9558   0.0066
 -10.250  -0.6669   0.02155   0.01597  -0.1011   0.9504   0.0068
 -10.000  -0.6355   0.02013   0.01444  -0.1048   0.9474   0.0073
  -9.750  -0.6129   0.01903   0.01326  -0.1059   0.9394   0.0077
  -9.500  -0.5812   0.01801   0.01219  -0.1084   0.9355   0.0083
  -9.250  -0.5471   0.01717   0.01128  -0.1110   0.9321   0.0093
  -9.000  -0.5180   0.01639   0.01045  -0.1126   0.9253   0.0102
  -8.750  -0.4816   0.01567   0.00968  -0.1154   0.9211   0.0119
  -8.500  -0.4417   0.01493   0.00890  -0.1189   0.9176   0.0141
  -8.250  -0.4072   0.01431   0.00825  -0.1212   0.9102   0.0166
  -8.000  -0.3651   0.01371   0.00761  -0.1250   0.9050   0.0201
  -7.750  -0.3256   0.01316   0.00702  -0.1282   0.8982   0.0248
  -7.500  -0.2876   0.01265   0.00649  -0.1310   0.8898   0.0307
  -7.000  -0.2168   0.01174   0.00553  -0.1354   0.8707   0.0491
  -6.750  -0.1862   0.01134   0.00513  -0.1366   0.8596   0.0628
  -6.500  -0.1554   0.01091   0.00473  -0.1377   0.8490   0.0812
  -6.000  -0.0967   0.01005   0.00396  -0.1395   0.8269   0.1364
  -5.750  -0.0679   0.00947   0.00351  -0.1404   0.8163   0.1886
  -5.500  -0.0389   0.00873   0.00304  -0.1416   0.8058   0.2766
  -5.250  -0.0104   0.00847   0.00289  -0.1421   0.7950   0.3283
  -5.000   0.0182   0.00840   0.00280  -0.1423   0.7850   0.3509
  -4.750   0.0465   0.00838   0.00272  -0.1424   0.7746   0.3650
  -4.500   0.0748   0.00838   0.00265  -0.1424   0.7645   0.3760
  -4.250   0.1030   0.00838   0.00260  -0.1424   0.7548   0.3844
  -4.000   0.1310   0.00841   0.00254  -0.1424   0.7444   0.3937
  -3.750   0.1592   0.00846   0.00254  -0.1424   0.7349   0.4065
  -3.500   0.1870   0.00850   0.00255  -0.1424   0.7249   0.4147
  -3.250   0.2150   0.00852   0.00249  -0.1424   0.7155   0.4182
  -3.000   0.2427   0.00855   0.00243  -0.1423   0.7059   0.4211
  -2.750   0.2707   0.00858   0.00237  -0.1423   0.6959   0.4238
  -2.500   0.2983   0.00859   0.00234  -0.1422   0.6866   0.4265
  -2.250   0.3259   0.00862   0.00232  -0.1421   0.6767   0.4291
  -2.000   0.3538   0.00864   0.00230  -0.1420   0.6675   0.4317
  -1.500   0.4090   0.00873   0.00226  -0.1419   0.6488   0.4374
  -1.250   0.4365   0.00879   0.00225  -0.1417   0.6399   0.4402
  -1.000   0.4642   0.00882   0.00226  -0.1417   0.6306   0.4428
  -0.750   0.4916   0.00887   0.00228  -0.1416   0.6219   0.4454
  -0.500   0.5190   0.00892   0.00230  -0.1415   0.6126   0.4481
  -0.250   0.5465   0.00898   0.00233  -0.1414   0.6042   0.4509
   0.000   0.5737   0.00905   0.00235  -0.1412   0.5949   0.4540
   0.250   0.6011   0.00913   0.00239  -0.1411   0.5861   0.4569
   0.500   0.6281   0.00920   0.00244  -0.1409   0.5773   0.4598
   0.750   0.6555   0.00926   0.00249  -0.1408   0.5683   0.4626
   1.000   0.6821   0.00935   0.00256  -0.1406   0.5593   0.4656
   1.250   0.7095   0.00943   0.00262  -0.1404   0.5502   0.4687
   1.500   0.7361   0.00954   0.00269  -0.1402   0.5413   0.4717
   1.750   0.7630   0.00963   0.00277  -0.1400   0.5319   0.4747
   2.000   0.7895   0.00972   0.00287  -0.1397   0.5229   0.4780
   2.250   0.8159   0.00983   0.00297  -0.1394   0.5132   0.4816
   2.500   0.8424   0.00994   0.00308  -0.1392   0.5035   0.4851
   2.750   0.8681   0.01009   0.00319  -0.1388   0.4936   0.4884
   3.000   0.8943   0.01021   0.00330  -0.1385   0.4830   0.4915
   3.250   0.9201   0.01034   0.00344  -0.1381   0.4727   0.4949
   3.500   0.9452   0.01051   0.00359  -0.1376   0.4620   0.4989
   3.750   0.9710   0.01065   0.00373  -0.1372   0.4509   0.5032
   4.000   0.9962   0.01082   0.00389  -0.1367   0.4405   0.5072
   4.250   1.0207   0.01100   0.00406  -0.1361   0.4295   0.5110
   4.500   1.0459   0.01116   0.00424  -0.1356   0.4183   0.5152
   4.750   1.0705   0.01135   0.00443  -0.1350   0.4074   0.5196
   5.000   1.0943   0.01157   0.00463  -0.1343   0.3959   0.5240
   5.250   1.1181   0.01178   0.00484  -0.1336   0.3835   0.5288
   5.500   1.1418   0.01200   0.00507  -0.1329   0.3711   0.5342
   5.750   1.1646   0.01226   0.00531  -0.1320   0.3577   0.5396
   6.000   1.1870   0.01252   0.00557  -0.1311   0.3447   0.5446
   6.250   1.2087   0.01281   0.00585  -0.1300   0.3309   0.5502
   6.500   1.2291   0.01312   0.00614  -0.1287   0.3164   0.5562
   6.750   1.2487   0.01344   0.00645  -0.1273   0.3015   0.5623
   7.000   1.2677   0.01379   0.00678  -0.1257   0.2857   0.5694
   7.250   1.2859   0.01419   0.00716  -0.1241   0.2686   0.5764
   7.500   1.3033   0.01464   0.00757  -0.1223   0.2505   0.5838
   7.750   1.3199   0.01513   0.00802  -0.1205   0.2325   0.5913
   8.000   1.3362   0.01565   0.00851  -0.1186   0.2154   0.5992
   8.250   1.3515   0.01621   0.00903  -0.1166   0.1989   0.6080
   8.500   1.3666   0.01678   0.00958  -0.1146   0.1837   0.6179
   8.750   1.3809   0.01739   0.01017  -0.1126   0.1689   0.6281
   9.000   1.3947   0.01802   0.01080  -0.1105   0.1551   0.6394
   9.250   1.4084   0.01866   0.01146  -0.1085   0.1432   0.6509
   9.500   1.4214   0.01935   0.01215  -0.1064   0.1320   0.6631
   9.750   1.4332   0.02011   0.01292  -0.1042   0.1213   0.6768
  10.000   1.4445   0.02091   0.01374  -0.1020   0.1105   0.6930
  10.250   1.4557   0.02173   0.01461  -0.0999   0.1007   0.7110
  10.500   1.4660   0.02261   0.01555  -0.0978   0.0922   0.7326
  11.000   1.4851   0.02450   0.01760  -0.0936   0.0777   0.7905
  11.250   1.4914   0.02550   0.01875  -0.0911   0.0719   0.8453
  11.500   1.4954   0.02635   0.01975  -0.0881   0.0669   1.0000
  11.750   1.5027   0.02769   0.02110  -0.0862   0.0616   1.0000
  12.000   1.5112   0.02900   0.02244  -0.0847   0.0567   1.0000
  12.250   1.5176   0.03052   0.02398  -0.0830   0.0524   1.0000
  12.500   1.5250   0.03202   0.02552  -0.0816   0.0484   1.0000
  13.000   1.5365   0.03547   0.02904  -0.0789   0.0413   1.0000
  13.250   1.5403   0.03747   0.03107  -0.0777   0.0380   1.0000
  13.500   1.5453   0.03942   0.03309  -0.0767   0.0353   1.0000
  13.750   1.5485   0.04163   0.03534  -0.0758   0.0325   1.0000
  14.000   1.5516   0.04394   0.03770  -0.0750   0.0303   1.0000
  14.250   1.5548   0.04629   0.04012  -0.0743   0.0281   1.0000
  14.500   1.5558   0.04898   0.04286  -0.0738   0.0261   1.0000
  14.750   1.5584   0.05158   0.04554  -0.0735   0.0245   1.0000
  15.000   1.5595   0.05443   0.04846  -0.0732   0.0228   1.0000
  15.250   1.5589   0.05758   0.05168  -0.0732   0.0215   1.0000
  15.500   1.5599   0.06061   0.05481  -0.0732   0.0202   1.0000
  15.750   1.5597   0.06391   0.05819  -0.0735   0.0189   1.0000
  16.000   1.5576   0.06754   0.06189  -0.0739   0.0179   1.0000
  16.250   1.5562   0.07116   0.06561  -0.0744   0.0169   1.0000
  16.500   1.5548   0.07488   0.06942  -0.0751   0.0160   1.0000
  16.750   1.5521   0.07888   0.07351  -0.0760   0.0151   1.0000
  17.000   1.5477   0.08321   0.07792  -0.0771   0.0144   1.0000
  17.250   1.5448   0.08740   0.08222  -0.0783   0.0137   1.0000
  17.500   1.5413   0.09176   0.08669  -0.0796   0.0130   1.0000
  17.750   1.5367   0.09637   0.09139  -0.0811   0.0124   1.0000
  18.000   1.5310   0.10122   0.09635  -0.0829   0.0118   1.0000
  18.250   1.5250   0.10621   0.10143  -0.0848   0.0114   1.0000
  18.500   1.5205   0.11097   0.10632  -0.0867   0.0109   1.0000
  18.750   1.5153   0.11592   0.11137  -0.0888   0.0104   1.0000
  19.000   1.5094   0.12103   0.11659  -0.0912   0.0100   1.0000
  19.250   1.5029   0.12630   0.12195  -0.0937   0.0096   1.0000
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