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EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 555 AIRFOIL (e555-il)
Reynolds number: 500,000
Max Cl/Cd: 93.43 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e555-il-500000.txt
Download as CSV file: xf-e555-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7308   0.07313   0.06960  -0.0668   1.0000   0.0108
 -14.000  -0.7410   0.06897   0.06531  -0.0688   1.0000   0.0107
 -13.750  -0.7467   0.06504   0.06133  -0.0693   1.0000   0.0105
 -13.500  -0.7580   0.06088   0.05706  -0.0704   1.0000   0.0104
 -13.250  -0.7708   0.05665   0.05269  -0.0714   1.0000   0.0103
 -13.000  -0.7802   0.05307   0.04898  -0.0720   1.0000   0.0102
 -12.750  -0.7895   0.04958   0.04534  -0.0723   1.0000   0.0101
 -12.500  -0.7973   0.04638   0.04199  -0.0721   1.0000   0.0099
 -12.250  -0.8022   0.04365   0.03911  -0.0716   1.0000   0.0098
 -12.000  -0.8065   0.04103   0.03635  -0.0706   1.0000   0.0097
 -11.750  -0.8094   0.03874   0.03391  -0.0692   1.0000   0.0096
 -11.500  -0.8108   0.03678   0.03184  -0.0676   1.0000   0.0096
 -11.250  -0.8120   0.03507   0.03002  -0.0656   1.0000   0.0095
 -11.000  -0.8145   0.03349   0.02834  -0.0631   1.0000   0.0095
 -10.750  -0.8200   0.03213   0.02692  -0.0600   1.0000   0.0095
 -10.500  -0.8322   0.03098   0.02571  -0.0559   1.0000   0.0095
 -10.250  -0.8188   0.02947   0.02410  -0.0562   0.9978   0.0095
 -10.000  -0.7920   0.02786   0.02239  -0.0589   0.9942   0.0096
  -9.750  -0.7656   0.02617   0.02061  -0.0616   0.9898   0.0098
  -9.500  -0.7352   0.02445   0.01880  -0.0652   0.9857   0.0100
  -9.250  -0.7040   0.02282   0.01708  -0.0687   0.9818   0.0103
  -9.000  -0.6755   0.02143   0.01560  -0.0711   0.9760   0.0105
  -8.750  -0.6436   0.01959   0.01369  -0.0748   0.9726   0.0111
  -8.500  -0.6176   0.01838   0.01244  -0.0763   0.9657   0.0116
  -8.250  -0.5836   0.01734   0.01134  -0.0789   0.9623   0.0127
  -8.000  -0.5478   0.01615   0.01009  -0.0821   0.9600   0.0143
  -7.750  -0.5203   0.01532   0.00922  -0.0829   0.9530   0.0169
  -7.500  -0.4860   0.01429   0.00820  -0.0853   0.9495   0.0227
  -7.250  -0.4495   0.01328   0.00724  -0.0881   0.9470   0.0376
  -7.000  -0.4182   0.01242   0.00651  -0.0897   0.9411   0.0616
  -6.750  -0.3831   0.01139   0.00572  -0.0923   0.9361   0.1091
  -6.500  -0.3437   0.00972   0.00460  -0.0968   0.9327   0.2268
  -6.250  -0.3090   0.00864   0.00402  -0.0995   0.9257   0.3539
  -6.000  -0.2703   0.00847   0.00389  -0.1019   0.9192   0.3899
  -5.750  -0.2326   0.00845   0.00382  -0.1039   0.9116   0.4102
  -5.500  -0.1959   0.00843   0.00372  -0.1057   0.9026   0.4212
  -5.250  -0.1621   0.00847   0.00363  -0.1068   0.8922   0.4304
  -5.000  -0.1281   0.00851   0.00362  -0.1080   0.8824   0.4392
  -4.750  -0.0968   0.00861   0.00357  -0.1086   0.8711   0.4469
  -4.500  -0.0676   0.00861   0.00355  -0.1087   0.8595   0.4528
  -4.250  -0.0377   0.00880   0.00364  -0.1090   0.8483   0.4619
  -4.000  -0.0088   0.00886   0.00366  -0.1090   0.8370   0.4687
  -3.750   0.0189   0.00886   0.00360  -0.1089   0.8250   0.4721
  -3.500   0.0473   0.00885   0.00349  -0.1090   0.8137   0.4749
  -3.250   0.0759   0.00886   0.00338  -0.1091   0.8027   0.4778
  -3.000   0.1038   0.00883   0.00326  -0.1090   0.7912   0.4804
  -2.750   0.1314   0.00877   0.00316  -0.1089   0.7800   0.4829
  -2.500   0.1593   0.00877   0.00310  -0.1089   0.7693   0.4853
  -2.250   0.1870   0.00877   0.00305  -0.1088   0.7583   0.4879
  -2.000   0.2147   0.00878   0.00300  -0.1087   0.7473   0.4908
  -1.750   0.2426   0.00882   0.00294  -0.1087   0.7370   0.4937
  -1.500   0.2704   0.00884   0.00288  -0.1086   0.7261   0.4961
  -1.250   0.2978   0.00879   0.00282  -0.1085   0.7157   0.4987
  -1.000   0.3253   0.00881   0.00280  -0.1084   0.7056   0.5012
  -0.750   0.3528   0.00883   0.00279  -0.1083   0.6949   0.5040
  -0.500   0.3804   0.00887   0.00279  -0.1082   0.6848   0.5071
  -0.250   0.4080   0.00894   0.00278  -0.1081   0.6748   0.5101
   0.000   0.4355   0.00895   0.00277  -0.1080   0.6642   0.5127
   0.250   0.4628   0.00895   0.00276  -0.1079   0.6543   0.5155
   0.500   0.4900   0.00900   0.00278  -0.1077   0.6440   0.5183
   0.750   0.5173   0.00904   0.00282  -0.1076   0.6336   0.5212
   1.000   0.5446   0.00911   0.00285  -0.1074   0.6238   0.5246
   1.250   0.5718   0.00919   0.00288  -0.1073   0.6132   0.5278
   1.500   0.5989   0.00921   0.00291  -0.1071   0.6029   0.5310
   1.750   0.6257   0.00928   0.00296  -0.1069   0.5926   0.5340
   2.000   0.6526   0.00934   0.00303  -0.1067   0.5816   0.5372
   2.250   0.6794   0.00942   0.00310  -0.1065   0.5706   0.5407
   2.500   0.7061   0.00954   0.00316  -0.1062   0.5598   0.5442
   2.750   0.7325   0.00960   0.00324  -0.1060   0.5484   0.5479
   3.000   0.7590   0.00968   0.00334  -0.1057   0.5372   0.5516
   3.250   0.7852   0.00979   0.00344  -0.1054   0.5263   0.5555
   3.500   0.8112   0.00993   0.00355  -0.1050   0.5147   0.5595
   3.750   0.8375   0.01002   0.00365  -0.1047   0.5029   0.5633
   4.000   0.8634   0.01012   0.00378  -0.1044   0.4913   0.5674
   4.250   0.8889   0.01027   0.00393  -0.1039   0.4797   0.5721
   4.500   0.9145   0.01043   0.00406  -0.1035   0.4676   0.5770
   4.750   0.9402   0.01054   0.00421  -0.1031   0.4555   0.5816
   5.000   0.9654   0.01069   0.00439  -0.1027   0.4435   0.5865
   5.250   0.9902   0.01088   0.00456  -0.1021   0.4312   0.5918
   5.750   1.0393   0.01124   0.00496  -0.1010   0.4049   0.6030
   6.000   1.0637   0.01145   0.00516  -0.1004   0.3913   0.6097
   6.250   1.0875   0.01165   0.00539  -0.0997   0.3772   0.6160
   6.500   1.1109   0.01189   0.00564  -0.0989   0.3625   0.6232
   6.750   1.1339   0.01214   0.00590  -0.0981   0.3476   0.6304
   7.000   1.1563   0.01241   0.00618  -0.0972   0.3317   0.6383
   7.250   1.1780   0.01273   0.00648  -0.0962   0.3142   0.6467
   7.500   1.1988   0.01307   0.00682  -0.0950   0.2959   0.6564
   7.750   1.2185   0.01346   0.00719  -0.0937   0.2768   0.6663
   8.000   1.2378   0.01387   0.00757  -0.0924   0.2551   0.6776
   8.250   1.2544   0.01438   0.00803  -0.0905   0.2327   0.6897
   8.500   1.2696   0.01486   0.00849  -0.0884   0.2117   0.7026
   8.750   1.2840   0.01539   0.00899  -0.0862   0.1926   0.7173
   9.000   1.2976   0.01596   0.00954  -0.0840   0.1751   0.7345
   9.250   1.3107   0.01656   0.01014  -0.0816   0.1588   0.7551
   9.500   1.3230   0.01715   0.01077  -0.0792   0.1439   0.7801
   9.750   1.3343   0.01773   0.01142  -0.0767   0.1302   0.8141
  10.000   1.3409   0.01819   0.01203  -0.0731   0.1185   0.8793
  10.250   1.3493   0.01873   0.01264  -0.0701   0.1076   1.0000
  10.500   1.3607   0.01956   0.01342  -0.0680   0.0969   1.0000
  10.750   1.3707   0.02047   0.01429  -0.0659   0.0873   1.0000
  11.000   1.3796   0.02146   0.01526  -0.0637   0.0785   1.0000
  11.250   1.3899   0.02241   0.01622  -0.0617   0.0712   1.0000
  11.500   1.3976   0.02354   0.01734  -0.0597   0.0645   1.0000
  11.750   1.4049   0.02475   0.01855  -0.0577   0.0585   1.0000
  12.000   1.4124   0.02600   0.01983  -0.0559   0.0533   1.0000
  12.250   1.4171   0.02751   0.02133  -0.0540   0.0485   1.0000
  12.500   1.4239   0.02893   0.02282  -0.0525   0.0445   1.0000
  12.750   1.4275   0.03067   0.02457  -0.0509   0.0407   1.0000
  13.000   1.4320   0.03242   0.02638  -0.0495   0.0375   1.0000
  13.250   1.4360   0.03428   0.02829  -0.0483   0.0347   1.0000
  13.500   1.4351   0.03667   0.03071  -0.0471   0.0322   1.0000
  13.750   1.4406   0.03858   0.03271  -0.0464   0.0299   1.0000
  14.000   1.4413   0.04101   0.03518  -0.0456   0.0281   1.0000
  14.250   1.4379   0.04398   0.03822  -0.0450   0.0264   1.0000
  14.500   1.4414   0.04635   0.04069  -0.0447   0.0248   1.0000
  14.750   1.4411   0.04921   0.04362  -0.0445   0.0234   1.0000
  15.000   1.4346   0.05291   0.04739  -0.0446   0.0222   1.0000
  15.250   1.4349   0.05596   0.05054  -0.0448   0.0210   1.0000
  15.500   1.4345   0.05918   0.05387  -0.0452   0.0200   1.0000
  15.750   1.4318   0.06279   0.05755  -0.0458   0.0190   1.0000
  16.000   1.4238   0.06726   0.06210  -0.0468   0.0182   1.0000
  16.250   1.4169   0.07174   0.06669  -0.0480   0.0175   1.0000
  16.500   1.4152   0.07559   0.07065  -0.0491   0.0167   1.0000
  16.750   1.4121   0.07974   0.07490  -0.0504   0.0160   1.0000
  17.000   1.4074   0.08424   0.07949  -0.0520   0.0154   1.0000
  17.250   1.3978   0.08963   0.08497  -0.0540   0.0149   1.0000
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