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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.96 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e558-il-1000000.txt
Download as CSV file: xf-e558-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 558 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.8127   0.08666   0.08340  -0.0543   1.0000   0.0090
 -16.000  -0.8193   0.08244   0.07913  -0.0561   1.0000   0.0090
 -15.750  -0.8241   0.07847   0.07509  -0.0578   1.0000   0.0091
 -15.500  -0.8284   0.07450   0.07108  -0.0596   1.0000   0.0092
 -15.250  -0.8347   0.07061   0.06713  -0.0611   1.0000   0.0091
 -15.000  -0.8410   0.06661   0.06306  -0.0628   1.0000   0.0094
 -14.750  -0.8485   0.06278   0.05917  -0.0643   1.0000   0.0092
 -14.500  -0.8573   0.05890   0.05523  -0.0657   1.0000   0.0093
 -14.250  -0.8678   0.05498   0.05124  -0.0670   1.0000   0.0095
 -14.000  -0.8791   0.05122   0.04741  -0.0681   1.0000   0.0094
 -13.750  -0.8897   0.04757   0.04370  -0.0691   1.0000   0.0094
 -13.500  -0.9013   0.04394   0.04000  -0.0699   1.0000   0.0096
 -13.250  -0.9168   0.04011   0.03610  -0.0705   1.0000   0.0095
 -13.000  -0.9318   0.03654   0.03247  -0.0708   1.0000   0.0095
 -12.750  -0.9484   0.03313   0.02898  -0.0705   1.0000   0.0095
 -12.500  -0.9788   0.02963   0.02539  -0.0689   1.0000   0.0095
 -12.250  -0.9585   0.02589   0.02150  -0.0765   0.9974   0.0096
 -12.000  -0.9264   0.02421   0.01971  -0.0808   0.9949   0.0098
 -11.750  -0.8979   0.02219   0.01757  -0.0847   0.9921   0.0100
 -11.500  -0.8713   0.02037   0.01565  -0.0875   0.9882   0.0102
 -11.250  -0.8397   0.01910   0.01430  -0.0901   0.9858   0.0106
 -11.000  -0.8054   0.01814   0.01329  -0.0927   0.9841   0.0108
 -10.750  -0.7699   0.01733   0.01243  -0.0953   0.9829   0.0112
 -10.500  -0.7455   0.01655   0.01159  -0.0954   0.9774   0.0115
 -10.250  -0.7127   0.01583   0.01081  -0.0971   0.9745   0.0118
 -10.000  -0.6776   0.01519   0.01012  -0.0991   0.9725   0.0122
  -9.750  -0.6514   0.01437   0.00924  -0.0994   0.9669   0.0128
  -9.500  -0.6211   0.01370   0.00854  -0.1004   0.9618   0.0135
  -9.250  -0.5866   0.01313   0.00793  -0.1021   0.9586   0.0144
  -9.000  -0.5638   0.01267   0.00743  -0.1012   0.9477   0.0150
  -8.750  -0.5325   0.01202   0.00677  -0.1022   0.9397   0.0169
  -8.500  -0.4931   0.01142   0.00615  -0.1048   0.9327   0.0202
  -8.250  -0.4463   0.01060   0.00539  -0.1093   0.9247   0.0345
  -8.000  -0.3985   0.00984   0.00472  -0.1141   0.9112   0.0572
  -7.750  -0.3604   0.00937   0.00426  -0.1165   0.8876   0.0759
  -7.500  -0.3310   0.00908   0.00392  -0.1169   0.8620   0.0926
  -7.250  -0.3051   0.00885   0.00366  -0.1166   0.8386   0.1078
  -7.000  -0.2799   0.00863   0.00342  -0.1161   0.8169   0.1240
  -6.750  -0.2547   0.00843   0.00320  -0.1156   0.7968   0.1411
  -6.500  -0.2291   0.00827   0.00302  -0.1151   0.7786   0.1571
  -6.250  -0.2031   0.00814   0.00286  -0.1147   0.7617   0.1718
  -6.000  -0.1769   0.00803   0.00272  -0.1143   0.7456   0.1857
  -5.750  -0.1504   0.00793   0.00259  -0.1140   0.7300   0.1999
  -5.500  -0.1237   0.00786   0.00249  -0.1137   0.7157   0.2129
  -5.250  -0.0970   0.00780   0.00240  -0.1133   0.7015   0.2257
  -5.000  -0.0698   0.00773   0.00231  -0.1131   0.6876   0.2374
  -4.750  -0.0423   0.00772   0.00223  -0.1129   0.6743   0.2450
  -4.500  -0.0151   0.00767   0.00216  -0.1127   0.6619   0.2538
  -4.250   0.0124   0.00769   0.00210  -0.1124   0.6492   0.2606
  -4.000   0.0400   0.00763   0.00203  -0.1123   0.6369   0.2692
  -3.750   0.0676   0.00764   0.00198  -0.1121   0.6253   0.2761
  -3.500   0.0950   0.00762   0.00192  -0.1119   0.6137   0.2838
  -3.250   0.1231   0.00761   0.00188  -0.1117   0.6031   0.2911
  -3.000   0.1506   0.00763   0.00185  -0.1116   0.5921   0.2982
  -2.750   0.1784   0.00762   0.00182  -0.1114   0.5811   0.3056
  -2.500   0.2064   0.00765   0.00179  -0.1113   0.5713   0.3115
  -2.250   0.2340   0.00765   0.00177  -0.1111   0.5612   0.3196
  -2.000   0.2621   0.00766   0.00176  -0.1110   0.5515   0.3266
  -1.750   0.2895   0.00770   0.00175  -0.1108   0.5413   0.3332
  -1.500   0.3177   0.00770   0.00174  -0.1107   0.5323   0.3406
  -1.250   0.3453   0.00777   0.00175  -0.1106   0.5233   0.3467
  -1.000   0.3734   0.00776   0.00175  -0.1105   0.5149   0.3543
  -0.750   0.4009   0.00782   0.00177  -0.1103   0.5058   0.3614
  -0.500   0.4290   0.00784   0.00178  -0.1102   0.4976   0.3684
  -0.250   0.4563   0.00790   0.00181  -0.1100   0.4890   0.3755
   0.000   0.4846   0.00793   0.00183  -0.1100   0.4819   0.3820
   0.250   0.5120   0.00798   0.00186  -0.1098   0.4737   0.3900
   0.500   0.5399   0.00802   0.00190  -0.1097   0.4665   0.3974
   0.750   0.5676   0.00807   0.00194  -0.1095   0.4589   0.4044
   1.000   0.5950   0.00813   0.00199  -0.1093   0.4521   0.4126
   1.250   0.6230   0.00818   0.00204  -0.1092   0.4456   0.4199
   1.500   0.6500   0.00825   0.00210  -0.1090   0.4384   0.4285
   1.750   0.6779   0.00830   0.00216  -0.1089   0.4324   0.4366
   2.000   0.7053   0.00835   0.00222  -0.1087   0.4257   0.4462
   2.250   0.7322   0.00846   0.00230  -0.1085   0.4193   0.4551
   2.500   0.7601   0.00848   0.00238  -0.1084   0.4142   0.4656
   2.750   0.7872   0.00856   0.00245  -0.1082   0.4081   0.4763
   3.000   0.8139   0.00865   0.00256  -0.1079   0.4018   0.4885
   3.250   0.8416   0.00869   0.00264  -0.1078   0.3970   0.5009
   3.500   0.8686   0.00876   0.00274  -0.1076   0.3916   0.5152
   3.750   0.8947   0.00888   0.00286  -0.1072   0.3855   0.5315
   4.000   0.9223   0.00891   0.00296  -0.1071   0.3811   0.5496
   4.250   0.9491   0.00897   0.00308  -0.1068   0.3759   0.5699
   4.500   0.9749   0.00908   0.00322  -0.1064   0.3700   0.5947
   4.750   1.0019   0.00912   0.00335  -0.1062   0.3656   0.6226
   5.000   1.0284   0.00917   0.00349  -0.1059   0.3605   0.6544
   5.500   1.0793   0.00929   0.00382  -0.1050   0.3503   0.7398
   5.750   1.1046   0.00928   0.00398  -0.1044   0.3459   0.7965
   6.000   1.1258   0.00924   0.00416  -0.1029   0.3410   0.8771
   6.250   1.1518   0.00928   0.00430  -0.1024   0.3351   1.0000
   6.500   1.1786   0.00939   0.00443  -0.1022   0.3310   1.0000
   6.750   1.2043   0.00955   0.00458  -0.1018   0.3254   1.0000
   7.000   1.2284   0.00979   0.00478  -0.1011   0.3190   1.0000
   7.250   1.2548   0.00991   0.00492  -0.1008   0.3148   1.0000
   7.500   1.2798   0.01008   0.00510  -0.1003   0.3091   1.0000
   7.750   1.3031   0.01034   0.00532  -0.0995   0.3027   1.0000
   8.000   1.3287   0.01047   0.00548  -0.0991   0.2982   1.0000
   8.250   1.3526   0.01069   0.00568  -0.0984   0.2918   1.0000
   8.500   1.3758   0.01093   0.00591  -0.0976   0.2841   1.0000
   8.750   1.3986   0.01117   0.00613  -0.0968   0.2753   1.0000
   9.000   1.4208   0.01143   0.00637  -0.0958   0.2669   1.0000
   9.250   1.4418   0.01169   0.00662  -0.0946   0.2593   1.0000
   9.500   1.4621   0.01197   0.00688  -0.0933   0.2517   1.0000
   9.750   1.4808   0.01230   0.00718  -0.0917   0.2422   1.0000
  10.000   1.4997   0.01262   0.00749  -0.0902   0.2326   1.0000
  10.250   1.5164   0.01304   0.00787  -0.0883   0.2213   1.0000
  10.500   1.5319   0.01351   0.00828  -0.0863   0.2091   1.0000
  10.750   1.5460   0.01404   0.00875  -0.0842   0.1955   1.0000
  11.000   1.5588   0.01464   0.00929  -0.0818   0.1812   1.0000
  11.250   1.5701   0.01529   0.00988  -0.0793   0.1673   1.0000
  11.500   1.5809   0.01598   0.01052  -0.0768   0.1548   1.0000
  11.750   1.5901   0.01675   0.01123  -0.0742   0.1422   1.0000
  12.000   1.5981   0.01759   0.01203  -0.0715   0.1304   1.0000
  12.250   1.6044   0.01854   0.01295  -0.0688   0.1191   1.0000
  12.500   1.6090   0.01962   0.01398  -0.0660   0.1082   1.0000
  12.750   1.6124   0.02083   0.01516  -0.0633   0.0983   1.0000
  13.000   1.6158   0.02212   0.01643  -0.0608   0.0897   1.0000
  13.250   1.6194   0.02349   0.01779  -0.0586   0.0820   1.0000
  13.500   1.6211   0.02508   0.01938  -0.0564   0.0750   1.0000
  13.750   1.6218   0.02685   0.02115  -0.0545   0.0686   1.0000
  14.000   1.6238   0.02864   0.02297  -0.0529   0.0630   1.0000
  14.250   1.6216   0.03089   0.02522  -0.0513   0.0573   1.0000
  14.500   1.6217   0.03309   0.02745  -0.0501   0.0528   1.0000
  14.750   1.6187   0.03567   0.03006  -0.0491   0.0482   1.0000
  15.000   1.6150   0.03846   0.03289  -0.0482   0.0441   1.0000
  15.250   1.6115   0.04138   0.03585  -0.0477   0.0404   1.0000
  15.500   1.6045   0.04476   0.03927  -0.0473   0.0369   1.0000
  15.750   1.5991   0.04813   0.04269  -0.0472   0.0335   1.0000
  16.000   1.5902   0.05203   0.04665  -0.0472   0.0304   1.0000
  16.250   1.5820   0.05598   0.05064  -0.0475   0.0273   1.0000
  16.500   1.5709   0.06044   0.05516  -0.0481   0.0240   1.0000
  16.750   1.5606   0.06493   0.05972  -0.0489   0.0219   1.0000
  17.000   1.5502   0.06957   0.06442  -0.0498   0.0197   1.0000
  17.250   1.5404   0.07426   0.06919  -0.0509   0.0183   1.0000
  17.500   1.5316   0.07893   0.07393  -0.0521   0.0171   1.0000
  17.750   1.5223   0.08374   0.07883  -0.0535   0.0163   1.0000
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