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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 500,000
Max Cl/Cd: 99.07 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e558-il-500000-n5.txt
Download as CSV file: xf-e558-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.7436   0.09759   0.09370  -0.0495   1.0000   0.0089
 -16.000  -0.7492   0.09322   0.08927  -0.0514   1.0000   0.0089
 -15.750  -0.7541   0.08904   0.08503  -0.0532   1.0000   0.0089
 -15.500  -0.7601   0.08478   0.08072  -0.0550   1.0000   0.0089
 -15.250  -0.7657   0.08068   0.07656  -0.0567   1.0000   0.0090
 -15.000  -0.7727   0.07639   0.07220  -0.0585   1.0000   0.0091
 -14.750  -0.7800   0.07223   0.06798  -0.0603   1.0000   0.0091
 -14.500  -0.7875   0.06811   0.06381  -0.0619   1.0000   0.0091
 -14.250  -0.7967   0.06395   0.05957  -0.0636   1.0000   0.0093
 -14.000  -0.8067   0.05997   0.05552  -0.0650   1.0000   0.0092
 -13.750  -0.8180   0.05594   0.05143  -0.0664   1.0000   0.0093
 -13.500  -0.8299   0.05200   0.04741  -0.0676   1.0000   0.0094
 -13.250  -0.8438   0.04799   0.04334  -0.0687   1.0000   0.0094
 -13.000  -0.8571   0.04424   0.03951  -0.0695   1.0000   0.0094
 -12.750  -0.8713   0.04058   0.03579  -0.0700   1.0000   0.0094
 -12.500  -0.8881   0.03694   0.03207  -0.0701   1.0000   0.0095
 -12.250  -0.9100   0.03338   0.02843  -0.0695   1.0000   0.0094
 -12.000  -0.8953   0.02918   0.02407  -0.0770   0.9956   0.0096
 -11.750  -0.8696   0.02627   0.02099  -0.0833   0.9912   0.0098
 -11.500  -0.8449   0.02427   0.01889  -0.0867   0.9865   0.0100
 -11.250  -0.8161   0.02265   0.01717  -0.0899   0.9833   0.0103
 -11.000  -0.7938   0.02148   0.01592  -0.0908   0.9773   0.0106
 -10.750  -0.7650   0.02045   0.01482  -0.0925   0.9728   0.0109
 -10.500  -0.7416   0.01955   0.01385  -0.0928   0.9659   0.0114
  -9.750  -0.6642   0.01716   0.01127  -0.0943   0.9415   0.0131
  -9.500  -0.6337   0.01644   0.01048  -0.0955   0.9333   0.0139
  -9.250  -0.5994   0.01577   0.00974  -0.0973   0.9257   0.0150
  -9.000  -0.5597   0.01502   0.00894  -0.1003   0.9174   0.0166
  -8.750  -0.5141   0.01432   0.00819  -0.1045   0.9090   0.0196
  -8.500  -0.4658   0.01363   0.00745  -0.1092   0.8964   0.0251
  -8.250  -0.4249   0.01300   0.00677  -0.1124   0.8775   0.0345
  -8.000  -0.3922   0.01248   0.00621  -0.1138   0.8543   0.0468
  -7.750  -0.3645   0.01206   0.00574  -0.1142   0.8318   0.0602
  -7.500  -0.3387   0.01171   0.00534  -0.1140   0.8104   0.0742
  -7.250  -0.3136   0.01140   0.00499  -0.1136   0.7908   0.0881
  -7.000  -0.2885   0.01113   0.00468  -0.1132   0.7724   0.1020
  -6.750  -0.2633   0.01088   0.00440  -0.1128   0.7553   0.1175
  -6.500  -0.2381   0.01061   0.00413  -0.1124   0.7392   0.1373
  -6.250  -0.2126   0.01035   0.00389  -0.1121   0.7242   0.1604
  -5.750  -0.1603   0.01004   0.00354  -0.1114   0.6959   0.1944
  -5.500  -0.1339   0.00993   0.00339  -0.1111   0.6826   0.2068
  -5.250  -0.1070   0.00985   0.00325  -0.1108   0.6697   0.2162
  -5.000  -0.0800   0.00979   0.00313  -0.1106   0.6572   0.2255
  -4.750  -0.0532   0.00973   0.00302  -0.1103   0.6449   0.2344
  -4.500  -0.0259   0.00969   0.00291  -0.1100   0.6330   0.2427
  -4.250   0.0013   0.00963   0.00282  -0.1098   0.6222   0.2507
  -4.000   0.0285   0.00962   0.00274  -0.1095   0.6111   0.2588
  -3.750   0.0558   0.00958   0.00266  -0.1093   0.5996   0.2663
  -3.500   0.0832   0.00957   0.00259  -0.1091   0.5895   0.2743
  -3.250   0.1106   0.00956   0.00253  -0.1089   0.5793   0.2810
  -3.000   0.1381   0.00954   0.00248  -0.1087   0.5693   0.2887
  -2.500   0.1930   0.00954   0.00240  -0.1083   0.5498   0.3029
  -2.250   0.2203   0.00957   0.00236  -0.1081   0.5409   0.3096
  -2.000   0.2480   0.00957   0.00234  -0.1080   0.5316   0.3166
  -1.750   0.2753   0.00960   0.00232  -0.1077   0.5226   0.3235
  -1.500   0.3031   0.00962   0.00231  -0.1076   0.5140   0.3298
  -1.250   0.3302   0.00965   0.00231  -0.1074   0.5060   0.3370
  -1.000   0.3580   0.00967   0.00231  -0.1072   0.4979   0.3438
  -0.500   0.4129   0.00974   0.00234  -0.1068   0.4819   0.3577
  -0.250   0.4403   0.00980   0.00236  -0.1066   0.4746   0.3642
   0.000   0.4676   0.00984   0.00240  -0.1065   0.4679   0.3709
   0.250   0.4951   0.00989   0.00243  -0.1063   0.4604   0.3786
   0.500   0.5221   0.00996   0.00248  -0.1060   0.4533   0.3853
   0.750   0.5497   0.01000   0.00252  -0.1059   0.4468   0.3926
   1.000   0.5769   0.01007   0.00258  -0.1056   0.4403   0.3999
   1.250   0.6039   0.01013   0.00265  -0.1054   0.4342   0.4077
   1.500   0.6313   0.01019   0.00271  -0.1052   0.4277   0.4155
   1.750   0.6580   0.01028   0.00279  -0.1049   0.4212   0.4229
   2.000   0.6852   0.01034   0.00287  -0.1047   0.4160   0.4319
   2.250   0.7124   0.01041   0.00295  -0.1045   0.4104   0.4402
   2.500   0.7389   0.01051   0.00305  -0.1042   0.4046   0.4490
   2.750   0.7658   0.01059   0.00315  -0.1040   0.3993   0.4583
   3.000   0.7927   0.01066   0.00326  -0.1037   0.3936   0.4693
   3.250   0.8190   0.01076   0.00338  -0.1034   0.3885   0.4794
   3.500   0.8455   0.01087   0.00351  -0.1031   0.3839   0.4911
   3.750   0.8722   0.01094   0.00363  -0.1028   0.3786   0.5042
   4.000   0.8983   0.01104   0.00378  -0.1025   0.3732   0.5182
   4.250   0.9240   0.01117   0.00393  -0.1020   0.3686   0.5329
   4.500   0.9506   0.01124   0.00408  -0.1017   0.3642   0.5505
   4.750   0.9766   0.01133   0.00424  -0.1014   0.3590   0.5703
   5.000   1.0018   0.01146   0.00442  -0.1009   0.3539   0.5922
   5.250   1.0274   0.01156   0.00460  -0.1004   0.3496   0.6179
   5.500   1.0530   0.01163   0.00480  -0.1000   0.3445   0.6482
   5.750   1.0775   0.01174   0.00500  -0.0993   0.3393   0.6823
   6.000   1.1013   0.01185   0.00522  -0.0986   0.3346   0.7236
   6.250   1.1252   0.01187   0.00544  -0.0977   0.3301   0.7769
   6.500   1.1454   0.01188   0.00565  -0.0961   0.3250   0.8482
   6.750   1.1703   0.01191   0.00582  -0.0954   0.3198   1.0000
   7.000   1.1954   0.01210   0.00603  -0.0949   0.3151   1.0000
   7.250   1.2196   0.01231   0.00625  -0.0943   0.3092   1.0000
   7.500   1.2422   0.01258   0.00650  -0.0934   0.3034   1.0000
   7.750   1.2663   0.01279   0.00673  -0.0928   0.2977   1.0000
   8.000   1.2890   0.01304   0.00699  -0.0919   0.2914   1.0000
   8.250   1.3103   0.01333   0.00726  -0.0908   0.2854   1.0000
   8.500   1.3322   0.01356   0.00752  -0.0897   0.2790   1.0000
   8.750   1.3515   0.01388   0.00783  -0.0883   0.2723   1.0000
   9.000   1.3721   0.01416   0.00813  -0.0870   0.2662   1.0000
   9.250   1.3902   0.01452   0.00848  -0.0854   0.2575   1.0000
   9.500   1.4086   0.01488   0.00884  -0.0839   0.2475   1.0000
   9.750   1.4249   0.01533   0.00926  -0.0821   0.2374   1.0000
  10.000   1.4408   0.01581   0.00971  -0.0802   0.2264   1.0000
  10.250   1.4557   0.01633   0.01021  -0.0783   0.2138   1.0000
  10.500   1.4691   0.01693   0.01077  -0.0762   0.2018   1.0000
  10.750   1.4799   0.01766   0.01145  -0.0738   0.1873   1.0000
  11.000   1.4901   0.01843   0.01218  -0.0715   0.1746   1.0000
  11.250   1.4986   0.01931   0.01302  -0.0690   0.1620   1.0000
  11.500   1.5052   0.02033   0.01399  -0.0664   0.1492   1.0000
  11.750   1.5095   0.02151   0.01513  -0.0638   0.1356   1.0000
  12.000   1.5131   0.02282   0.01640  -0.0613   0.1237   1.0000
  12.500   1.5181   0.02581   0.01936  -0.0569   0.1025   1.0000
  12.750   1.5213   0.02742   0.02098  -0.0551   0.0951   1.0000
  13.000   1.5213   0.02937   0.02293  -0.0533   0.0872   1.0000
  13.250   1.5232   0.03130   0.02489  -0.0520   0.0804   1.0000
  13.500   1.5233   0.03350   0.02712  -0.0507   0.0749   1.0000
  13.750   1.5228   0.03585   0.02950  -0.0497   0.0692   1.0000
  14.000   1.5217   0.03839   0.03209  -0.0489   0.0646   1.0000
  14.250   1.5188   0.04123   0.03497  -0.0483   0.0595   1.0000
  14.500   1.5161   0.04415   0.03795  -0.0479   0.0556   1.0000
  14.750   1.5109   0.04746   0.04130  -0.0477   0.0513   1.0000
  15.000   1.5066   0.05080   0.04471  -0.0477   0.0479   1.0000
  15.250   1.5018   0.05430   0.04828  -0.0479   0.0448   1.0000
  15.500   1.4945   0.05822   0.05226  -0.0483   0.0417   1.0000
  15.750   1.4889   0.06206   0.05618  -0.0488   0.0389   1.0000
  16.000   1.4807   0.06633   0.06050  -0.0495   0.0362   1.0000
  16.250   1.4754   0.07033   0.06459  -0.0503   0.0342   1.0000
  16.500   1.4670   0.07485   0.06918  -0.0514   0.0317   1.0000
  16.750   1.4603   0.07924   0.07364  -0.0525   0.0297   1.0000
  17.000   1.4531   0.08375   0.07823  -0.0538   0.0277   1.0000
  17.250   1.4453   0.08848   0.08303  -0.0552   0.0259   1.0000
  17.500   1.4386   0.09310   0.08773  -0.0566   0.0239   1.0000
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