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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 200,000
Max Cl/Cd: 70.94 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e558-il-200000-n5.txt
Download as CSV file: xf-e558-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.5830   0.13468   0.13029  -0.0348   1.0000   0.0150
 -16.500  -0.6087   0.12476   0.12022  -0.0395   1.0000   0.0148
 -16.250  -0.6366   0.11469   0.10994  -0.0447   1.0000   0.0150
 -16.000  -0.6504   0.10806   0.10317  -0.0479   1.0000   0.0150
 -15.750  -0.6605   0.10241   0.09742  -0.0507   1.0000   0.0151
 -15.500  -0.6652   0.09801   0.09297  -0.0526   1.0000   0.0152
 -15.250  -0.6701   0.09366   0.08855  -0.0544   1.0000   0.0152
 -15.000  -0.6735   0.08969   0.08457  -0.0562   1.0000   0.0156
 -14.750  -0.6774   0.08570   0.08051  -0.0578   1.0000   0.0156
 -14.500  -0.6815   0.08174   0.07650  -0.0595   1.0000   0.0158
 -14.250  -0.6872   0.07754   0.07224  -0.0614   1.0000   0.0162
 -14.000  -0.6900   0.07405   0.06870  -0.0627   1.0000   0.0162
 -13.750  -0.6946   0.07039   0.06497  -0.0641   1.0000   0.0165
 -13.500  -0.6999   0.06680   0.06131  -0.0654   1.0000   0.0168
 -13.250  -0.7045   0.06353   0.05799  -0.0663   1.0000   0.0169
 -13.000  -0.7093   0.06032   0.05472  -0.0672   1.0000   0.0170
 -12.750  -0.7145   0.05717   0.05150  -0.0679   1.0000   0.0172
 -12.500  -0.7207   0.05404   0.04831  -0.0686   1.0000   0.0174
 -12.250  -0.7272   0.05098   0.04520  -0.0690   1.0000   0.0175
 -12.000  -0.7347   0.04796   0.04212  -0.0694   1.0000   0.0177
 -11.750  -0.7442   0.04490   0.03900  -0.0695   1.0000   0.0179
 -11.500  -0.7546   0.04198   0.03602  -0.0693   1.0000   0.0181
 -11.250  -0.7703   0.03894   0.03295  -0.0687   1.0000   0.0182
 -11.000  -0.7908   0.03619   0.03015  -0.0672   1.0000   0.0182
 -10.750  -0.8080   0.03325   0.02712  -0.0669   1.0000   0.0183
 -10.500  -0.7917   0.03062   0.02439  -0.0707   0.9961   0.0188
 -10.250  -0.7629   0.02853   0.02218  -0.0750   0.9901   0.0195
 -10.000  -0.7328   0.02679   0.02029  -0.0785   0.9842   0.0206
  -9.750  -0.7054   0.02526   0.01863  -0.0809   0.9771   0.0219
  -9.500  -0.6740   0.02385   0.01714  -0.0837   0.9712   0.0238
  -9.250  -0.6484   0.02263   0.01582  -0.0848   0.9619   0.0262
  -9.000  -0.6206   0.02151   0.01461  -0.0861   0.9534   0.0294
  -8.750  -0.5901   0.02035   0.01339  -0.0879   0.9459   0.0347
  -8.500  -0.5635   0.01930   0.01233  -0.0887   0.9357   0.0419
  -8.000  -0.5015   0.01739   0.01045  -0.0916   0.9187   0.0710
  -7.750  -0.4673   0.01655   0.00966  -0.0935   0.9107   0.0903
  -7.500  -0.4319   0.01582   0.00896  -0.0955   0.9016   0.1115
  -7.250  -0.3940   0.01516   0.00836  -0.0981   0.8924   0.1374
  -7.000  -0.3539   0.01462   0.00785  -0.1009   0.8824   0.1643
  -6.750  -0.3157   0.01420   0.00743  -0.1032   0.8698   0.1850
  -6.500  -0.2764   0.01388   0.00705  -0.1055   0.8563   0.2021
  -6.250  -0.2386   0.01363   0.00671  -0.1075   0.8414   0.2168
  -6.000  -0.2035   0.01345   0.00639  -0.1089   0.8251   0.2295
  -5.750  -0.1713   0.01330   0.00614  -0.1097   0.8086   0.2408
  -5.500  -0.1411   0.01318   0.00591  -0.1101   0.7920   0.2507
  -5.250  -0.1120   0.01311   0.00568  -0.1102   0.7756   0.2606
  -5.000  -0.0841   0.01301   0.00552  -0.1101   0.7600   0.2693
  -4.750  -0.0562   0.01296   0.00532  -0.1099   0.7450   0.2782
  -4.500  -0.0288   0.01290   0.00520  -0.1097   0.7308   0.2866
  -4.250  -0.0012   0.01287   0.00502  -0.1095   0.7170   0.2951
  -4.000   0.0257   0.01282   0.00491  -0.1092   0.7034   0.3027
  -3.750   0.0529   0.01280   0.00476  -0.1089   0.6902   0.3111
  -3.500   0.0797   0.01276   0.00468  -0.1086   0.6776   0.3183
  -3.250   0.1068   0.01277   0.00456  -0.1083   0.6655   0.3263
  -3.000   0.1337   0.01274   0.00448  -0.1080   0.6532   0.3333
  -2.750   0.1607   0.01273   0.00440  -0.1077   0.6419   0.3410
  -2.500   0.1876   0.01275   0.00431  -0.1073   0.6307   0.3483
  -2.250   0.2144   0.01273   0.00427  -0.1070   0.6192   0.3555
  -2.000   0.2415   0.01276   0.00420  -0.1067   0.6090   0.3633
  -1.750   0.2683   0.01276   0.00417  -0.1064   0.5983   0.3701
  -1.500   0.2952   0.01279   0.00414  -0.1061   0.5881   0.3780
  -1.250   0.3220   0.01282   0.00410  -0.1058   0.5782   0.3853
  -1.000   0.3489   0.01284   0.00411  -0.1055   0.5686   0.3926
  -0.750   0.3758   0.01291   0.00408  -0.1052   0.5596   0.4009
  -0.500   0.4026   0.01291   0.00411  -0.1049   0.5502   0.4083
   0.000   0.4561   0.01301   0.00414  -0.1042   0.5326   0.4242
   0.250   0.4827   0.01309   0.00417  -0.1039   0.5246   0.4330
   0.500   0.5095   0.01313   0.00423  -0.1036   0.5161   0.4412
   0.750   0.5359   0.01321   0.00428  -0.1033   0.5082   0.4503
   1.000   0.5627   0.01327   0.00435  -0.1030   0.5004   0.4595
   1.250   0.5892   0.01335   0.00443  -0.1026   0.4930   0.4691
   1.500   0.6156   0.01343   0.00451  -0.1023   0.4860   0.4788
   1.750   0.6421   0.01351   0.00461  -0.1020   0.4784   0.4900
   2.000   0.6681   0.01362   0.00471  -0.1015   0.4718   0.5010
   2.250   0.6948   0.01369   0.00484  -0.1013   0.4650   0.5131
   2.500   0.7208   0.01379   0.00497  -0.1009   0.4584   0.5264
   2.750   0.7467   0.01390   0.00511  -0.1004   0.4523   0.5406
   3.000   0.7728   0.01399   0.00527  -0.1000   0.4455   0.5562
   3.250   0.7984   0.01411   0.00542  -0.0996   0.4396   0.5736
   3.500   0.8241   0.01422   0.00561  -0.0991   0.4342   0.5935
   3.750   0.8497   0.01431   0.00581  -0.0986   0.4280   0.6160
   4.000   0.8745   0.01443   0.00599  -0.0980   0.4223   0.6417
   4.250   0.8992   0.01454   0.00621  -0.0973   0.4170   0.6720
   4.500   0.9233   0.01462   0.00644  -0.0965   0.4115   0.7079
   4.750   0.9460   0.01470   0.00666  -0.0954   0.4062   0.7522
   5.000   0.9677   0.01477   0.00687  -0.0939   0.4014   0.8101
   5.250   0.9905   0.01473   0.00705  -0.0926   0.3958   0.9108
   5.500   1.0199   0.01491   0.00724  -0.0930   0.3903   1.0000
   6.000   1.0702   0.01542   0.00775  -0.0922   0.3801   1.0000
   6.250   1.0949   0.01568   0.00802  -0.0917   0.3747   1.0000
   6.500   1.1191   0.01598   0.00828  -0.0911   0.3698   1.0000
   6.750   1.1434   0.01625   0.00859  -0.0905   0.3645   1.0000
   7.000   1.1673   0.01652   0.00891  -0.0899   0.3589   1.0000
   7.250   1.1905   0.01683   0.00920  -0.0892   0.3539   1.0000
   7.500   1.2138   0.01714   0.00955  -0.0884   0.3488   1.0000
   7.750   1.2365   0.01743   0.00990  -0.0876   0.3430   1.0000
   8.000   1.2584   0.01776   0.01024  -0.0867   0.3377   1.0000
   8.250   1.2802   0.01810   0.01062  -0.0857   0.3323   1.0000
   8.500   1.3013   0.01842   0.01100  -0.0847   0.3261   1.0000
   8.750   1.3209   0.01879   0.01137  -0.0834   0.3203   1.0000
   9.000   1.3406   0.01913   0.01180  -0.0821   0.3141   1.0000
   9.250   1.3582   0.01949   0.01221  -0.0805   0.3077   1.0000
   9.500   1.3744   0.01991   0.01263  -0.0786   0.3019   1.0000
   9.750   1.3913   0.02030   0.01313  -0.0769   0.2949   1.0000
  10.000   1.4059   0.02077   0.01361  -0.0749   0.2884   1.0000
  10.250   1.4212   0.02124   0.01416  -0.0731   0.2812   1.0000
  10.500   1.4341   0.02178   0.01475  -0.0710   0.2736   1.0000
  10.750   1.4470   0.02235   0.01539  -0.0690   0.2656   1.0000
  11.000   1.4573   0.02304   0.01609  -0.0667   0.2570   1.0000
  11.250   1.4689   0.02374   0.01687  -0.0647   0.2485   1.0000
  11.500   1.4764   0.02462   0.01776  -0.0624   0.2401   1.0000
  11.750   1.4865   0.02549   0.01872  -0.0605   0.2309   1.0000
  12.000   1.4923   0.02659   0.01985  -0.0583   0.2219   1.0000
  12.250   1.4968   0.02786   0.02115  -0.0562   0.2115   1.0000
  12.500   1.5003   0.02929   0.02261  -0.0543   0.2003   1.0000
  12.750   1.5008   0.03102   0.02436  -0.0524   0.1890   1.0000
  13.000   1.4987   0.03308   0.02642  -0.0507   0.1776   1.0000
  13.250   1.4937   0.03554   0.02887  -0.0491   0.1654   1.0000
  13.500   1.4892   0.03815   0.03150  -0.0480   0.1538   1.0000
  13.750   1.4838   0.04100   0.03438  -0.0471   0.1431   1.0000
  14.000   1.4767   0.04418   0.03758  -0.0465   0.1334   1.0000
  14.250   1.4674   0.04777   0.04118  -0.0461   0.1248   1.0000
  14.500   1.4623   0.05106   0.04454  -0.0460   0.1170   1.0000
  14.750   1.4533   0.05494   0.04846  -0.0462   0.1102   1.0000
  15.000   1.4459   0.05878   0.05236  -0.0465   0.1034   1.0000
  15.250   1.4367   0.06298   0.05662  -0.0471   0.0979   1.0000
  15.500   1.4292   0.06709   0.06081  -0.0478   0.0921   1.0000
  15.750   1.4192   0.07169   0.06546  -0.0488   0.0872   1.0000
  16.000   1.4125   0.07594   0.06979  -0.0497   0.0821   1.0000
  16.250   1.4022   0.08080   0.07472  -0.0511   0.0777   1.0000
  16.500   1.3954   0.08528   0.07928  -0.0523   0.0732   1.0000
  16.750   1.3866   0.09013   0.08420  -0.0538   0.0690   1.0000
  17.000   1.3782   0.09500   0.08915  -0.0554   0.0654   1.0000
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