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EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 555 AIRFOIL (e555-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.71 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e555-il-1000000.txt
Download as CSV file: xf-e555-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 555 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.7006   0.11734   0.11511  -0.0382   1.0000   0.0059
 -16.500  -0.7301   0.10677   0.10438  -0.0437   1.0000   0.0058
 -16.250  -0.7622   0.09650   0.09393  -0.0489   1.0000   0.0057
 -16.000  -0.7768   0.08997   0.08728  -0.0523   1.0000   0.0057
 -15.750  -0.7919   0.08371   0.08089  -0.0554   1.0000   0.0057
 -15.500  -0.8080   0.07755   0.07459  -0.0582   1.0000   0.0056
 -15.250  -0.8194   0.07243   0.06935  -0.0605   1.0000   0.0056
 -15.000  -0.8340   0.06711   0.06388  -0.0626   1.0000   0.0055
 -14.750  -0.8448   0.06256   0.05919  -0.0642   1.0000   0.0055
 -14.500  -0.8501   0.05894   0.05546  -0.0654   1.0000   0.0055
 -14.250  -0.8560   0.05537   0.05178  -0.0663   1.0000   0.0055
 -14.000  -0.8604   0.05217   0.04847  -0.0670   1.0000   0.0055
 -13.750  -0.8653   0.04912   0.04532  -0.0673   1.0000   0.0055
 -13.500  -0.8646   0.04679   0.04291  -0.0675   1.0000   0.0055
 -13.250  -0.8672   0.04422   0.04025  -0.0674   1.0000   0.0056
 -13.000  -0.8657   0.04215   0.03811  -0.0673   1.0000   0.0056
 -12.750  -0.8686   0.03980   0.03566  -0.0665   1.0000   0.0056
 -12.500  -0.8681   0.03786   0.03365  -0.0658   1.0000   0.0056
 -12.250  -0.8690   0.03594   0.03165  -0.0647   1.0000   0.0056
 -12.000  -0.8692   0.03421   0.02987  -0.0635   1.0000   0.0057
 -11.750  -0.8728   0.03243   0.02803  -0.0617   1.0000   0.0057
 -11.500  -0.8768   0.03090   0.02644  -0.0595   1.0000   0.0057
 -11.250  -0.8720   0.02924   0.02472  -0.0592   0.9993   0.0057
 -11.000  -0.8498   0.02724   0.02264  -0.0624   0.9967   0.0057
 -10.750  -0.8255   0.02533   0.02064  -0.0660   0.9940   0.0057
 -10.500  -0.8062   0.02343   0.01866  -0.0687   0.9891   0.0058
 -10.250  -0.7771   0.02149   0.01663  -0.0731   0.9855   0.0058
 -10.000  -0.7428   0.01970   0.01475  -0.0782   0.9834   0.0059
  -9.750  -0.7209   0.01841   0.01339  -0.0793   0.9764   0.0059
  -9.500  -0.6895   0.01729   0.01220  -0.0819   0.9736   0.0060
  -9.250  -0.6625   0.01637   0.01122  -0.0831   0.9687   0.0061
  -9.000  -0.6343   0.01533   0.01011  -0.0847   0.9637   0.0063
  -8.750  -0.6029   0.01416   0.00887  -0.0870   0.9607   0.0067
  -8.500  -0.5757   0.01347   0.00814  -0.0877   0.9544   0.0069
  -8.250  -0.5431   0.01284   0.00747  -0.0893   0.9498   0.0076
  -8.000  -0.5056   0.01218   0.00675  -0.0920   0.9470   0.0086
  -7.750  -0.4704   0.01154   0.00609  -0.0943   0.9410   0.0112
  -7.500  -0.4300   0.01087   0.00545  -0.0977   0.9358   0.0186
  -7.250  -0.3858   0.01028   0.00491  -0.1018   0.9311   0.0316
  -7.000  -0.3495   0.00979   0.00447  -0.1042   0.9205   0.0469
  -6.750  -0.3141   0.00928   0.00404  -0.1064   0.9091   0.0705
  -6.500  -0.2822   0.00877   0.00362  -0.1079   0.8960   0.1038
  -6.250  -0.2535   0.00818   0.00318  -0.1088   0.8828   0.1553
  -6.000  -0.2285   0.00711   0.00253  -0.1094   0.8695   0.2675
  -5.750  -0.2023   0.00655   0.00225  -0.1097   0.8570   0.3520
  -5.500  -0.1744   0.00644   0.00217  -0.1098   0.8452   0.3816
  -5.250  -0.1463   0.00643   0.00211  -0.1098   0.8331   0.3966
  -4.750  -0.0905   0.00644   0.00199  -0.1097   0.8086   0.4120
  -4.500  -0.0625   0.00646   0.00194  -0.1097   0.7971   0.4203
  -4.250  -0.0346   0.00649   0.00191  -0.1096   0.7858   0.4261
  -4.000  -0.0066   0.00656   0.00188  -0.1096   0.7743   0.4312
  -3.750   0.0213   0.00657   0.00189  -0.1095   0.7633   0.4398
  -3.500   0.0494   0.00668   0.00190  -0.1095   0.7525   0.4461
  -3.250   0.0772   0.00668   0.00184  -0.1094   0.7413   0.4488
  -3.000   0.1052   0.00666   0.00178  -0.1094   0.7307   0.4517
  -2.750   0.1330   0.00668   0.00175  -0.1094   0.7201   0.4542
  -2.500   0.1610   0.00670   0.00172  -0.1093   0.7095   0.4566
  -2.250   0.1892   0.00673   0.00170  -0.1094   0.6993   0.4590
  -2.000   0.2170   0.00677   0.00167  -0.1093   0.6892   0.4612
  -1.750   0.2452   0.00681   0.00165  -0.1093   0.6789   0.4631
  -1.500   0.2731   0.00680   0.00162  -0.1093   0.6693   0.4662
  -1.000   0.3290   0.00685   0.00161  -0.1093   0.6492   0.4713
  -0.750   0.3569   0.00690   0.00162  -0.1093   0.6396   0.4737
  -0.500   0.3848   0.00695   0.00163  -0.1093   0.6292   0.4761
  -0.250   0.4129   0.00700   0.00164  -0.1093   0.6197   0.4783
   0.000   0.4405   0.00706   0.00165  -0.1092   0.6098   0.4808
   0.250   0.4685   0.00707   0.00166  -0.1093   0.5998   0.4840
   0.500   0.4963   0.00712   0.00170  -0.1092   0.5900   0.4867
   0.750   0.5238   0.00719   0.00173  -0.1091   0.5797   0.4893
   1.000   0.5517   0.00725   0.00177  -0.1091   0.5695   0.4919
   1.250   0.5792   0.00734   0.00181  -0.1090   0.5593   0.4943
   1.500   0.6066   0.00741   0.00186  -0.1089   0.5481   0.4969
   1.750   0.6342   0.00746   0.00191  -0.1089   0.5373   0.5004
   2.000   0.6615   0.00754   0.00197  -0.1088   0.5265   0.5035
   2.250   0.6886   0.00764   0.00204  -0.1086   0.5152   0.5065
   2.500   0.7161   0.00773   0.00211  -0.1086   0.5043   0.5094
   2.750   0.7432   0.00784   0.00219  -0.1084   0.4933   0.5118
   3.000   0.7699   0.00794   0.00227  -0.1082   0.4815   0.5154
   3.250   0.7970   0.00803   0.00237  -0.1081   0.4698   0.5190
   3.500   0.8239   0.00814   0.00247  -0.1079   0.4585   0.5227
   3.750   0.8505   0.00828   0.00258  -0.1077   0.4469   0.5261
   4.250   0.9035   0.00853   0.00281  -0.1072   0.4227   0.5334
   4.500   0.9299   0.00867   0.00294  -0.1070   0.4111   0.5373
   4.750   0.9558   0.00883   0.00308  -0.1066   0.3983   0.5415
   5.000   0.9814   0.00902   0.00324  -0.1063   0.3854   0.5453
   5.250   1.0071   0.00918   0.00340  -0.1059   0.3720   0.5503
   5.500   1.0325   0.00937   0.00357  -0.1055   0.3577   0.5552
   5.750   1.0578   0.00957   0.00375  -0.1051   0.3439   0.5599
   6.000   1.0827   0.00978   0.00394  -0.1046   0.3296   0.5649
   6.250   1.1072   0.01001   0.00415  -0.1040   0.3146   0.5705
   6.500   1.1310   0.01028   0.00438  -0.1034   0.2974   0.5763
   6.750   1.1541   0.01058   0.00463  -0.1026   0.2791   0.5826
   7.000   1.1769   0.01090   0.00491  -0.1018   0.2606   0.5896
   7.250   1.1988   0.01127   0.00521  -0.1008   0.2389   0.5963
   7.500   1.2191   0.01172   0.00557  -0.0996   0.2159   0.6038
   7.750   1.2396   0.01214   0.00592  -0.0984   0.1955   0.6115
   8.000   1.2594   0.01257   0.00631  -0.0971   0.1765   0.6201
   8.250   1.2790   0.01301   0.00670  -0.0958   0.1603   0.6291
   8.500   1.2975   0.01348   0.00712  -0.0943   0.1442   0.6396
   9.250   1.3452   0.01486   0.00843  -0.0883   0.1039   0.6749
   9.500   1.3607   0.01534   0.00891  -0.0863   0.0935   0.6889
   9.750   1.3758   0.01583   0.00942  -0.0843   0.0838   0.7043
  10.000   1.3900   0.01636   0.00996  -0.0822   0.0754   0.7219
  10.500   1.4167   0.01748   0.01117  -0.0779   0.0605   0.7684
  10.750   1.4286   0.01807   0.01184  -0.0756   0.0540   0.8021
  11.000   1.4380   0.01865   0.01256  -0.0728   0.0486   0.8604
  11.250   1.4445   0.01910   0.01319  -0.0695   0.0438   1.0000
  11.500   1.4541   0.01997   0.01404  -0.0673   0.0388   1.0000
  11.750   1.4645   0.02083   0.01490  -0.0652   0.0347   1.0000
  12.000   1.4741   0.02176   0.01585  -0.0632   0.0314   1.0000
  12.250   1.4823   0.02282   0.01690  -0.0611   0.0279   1.0000
  12.500   1.4914   0.02387   0.01798  -0.0593   0.0254   1.0000
  12.750   1.4992   0.02505   0.01918  -0.0575   0.0232   1.0000
  13.000   1.5067   0.02631   0.02048  -0.0558   0.0213   1.0000
  13.250   1.5144   0.02761   0.02181  -0.0543   0.0198   1.0000
  13.500   1.5191   0.02919   0.02342  -0.0526   0.0181   1.0000
  13.750   1.5262   0.03066   0.02495  -0.0514   0.0169   1.0000
  14.000   1.5317   0.03232   0.02666  -0.0501   0.0157   1.0000
  14.250   1.5344   0.03429   0.02867  -0.0489   0.0145   1.0000
  14.500   1.5400   0.03609   0.03055  -0.0480   0.0138   1.0000
  14.750   1.5441   0.03810   0.03262  -0.0472   0.0129   1.0000
  15.000   1.5461   0.04037   0.03495  -0.0465   0.0122   1.0000
  15.250   1.5459   0.04299   0.03762  -0.0459   0.0114   1.0000
  15.500   1.5495   0.04531   0.04002  -0.0456   0.0109   1.0000
  15.750   1.5512   0.04789   0.04268  -0.0454   0.0104   1.0000
  16.000   1.5513   0.05076   0.04562  -0.0453   0.0099   1.0000
  16.250   1.5493   0.05400   0.04894  -0.0455   0.0094   1.0000
  16.500   1.5459   0.05752   0.05255  -0.0458   0.0089   1.0000
  16.750   1.5458   0.06073   0.05585  -0.0463   0.0086   1.0000
  17.000   1.5445   0.06420   0.05941  -0.0470   0.0083   1.0000
  17.250   1.5412   0.06804   0.06334  -0.0479   0.0080   1.0000
  17.500   1.5368   0.07216   0.06754  -0.0490   0.0076   1.0000
  17.750   1.5304   0.07666   0.07213  -0.0504   0.0073   1.0000
  18.000   1.5216   0.08169   0.07726  -0.0521   0.0070   1.0000
  18.250   1.5146   0.08658   0.08225  -0.0539   0.0068   1.0000
  18.500   1.5085   0.09139   0.08718  -0.0557   0.0066   1.0000
  18.750   1.5021   0.09636   0.09225  -0.0578   0.0064   1.0000
  19.000   1.4949   0.10155   0.09755  -0.0600   0.0062   1.0000
  19.250   1.4859   0.10713   0.10324  -0.0626   0.0061   1.0000
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