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EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 557 AIRFOIL (e557-il)
Reynolds number: 50,000
Max Cl/Cd: 25.42 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e557-il-50000.txt
Download as CSV file: xf-e557-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 557 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3113   0.10925   0.10307  -0.0414   1.0000   0.1765
 -10.000  -0.5184   0.08513   0.07869  -0.0638   1.0000   0.1141
  -9.750  -0.5345   0.08079   0.07439  -0.0635   1.0000   0.1132
  -9.500  -0.5557   0.07685   0.07053  -0.0627   1.0000   0.1122
  -9.250  -0.5846   0.07344   0.06722  -0.0612   1.0000   0.1107
  -9.000  -0.6165   0.06959   0.06339  -0.0608   1.0000   0.1083
  -8.750  -0.6485   0.06517   0.05885  -0.0611   1.0000   0.1060
  -8.500  -0.6732   0.06054   0.05393  -0.0616   1.0000   0.1042
  -8.250  -0.6811   0.05667   0.04978  -0.0617   1.0000   0.1047
  -8.000  -0.6805   0.05313   0.04595  -0.0618   1.0000   0.1064
  -7.750  -0.6746   0.04964   0.04207  -0.0622   1.0000   0.1089
  -7.500  -0.6631   0.04613   0.03801  -0.0629   1.0000   0.1119
  -7.250  -0.6477   0.04307   0.03466  -0.0628   1.0000   0.1167
  -7.000  -0.6307   0.04097   0.03246  -0.0621   1.0000   0.1244
  -6.750  -0.6128   0.03867   0.03003  -0.0614   1.0000   0.1334
  -6.500  -0.5942   0.03676   0.02799  -0.0606   1.0000   0.1456
  -6.250  -0.5772   0.03507   0.02643  -0.0592   1.0000   0.1619
  -6.000  -0.5600   0.03341   0.02498  -0.0580   1.0000   0.1848
  -5.750  -0.5404   0.03139   0.02343  -0.0580   1.0000   0.2254
  -5.500  -0.5222   0.03102   0.02436  -0.0564   1.0000   0.3204
  -5.250  -0.5177   0.03512   0.02886  -0.0480   1.0000   0.3989
  -5.000  -0.5132   0.03864   0.03235  -0.0402   1.0000   0.4422
  -4.750  -0.5126   0.04177   0.03551  -0.0310   1.0000   0.4646
  -4.500  -0.5064   0.04372   0.03736  -0.0250   1.0000   0.4926
  -4.250  -0.5038   0.04560   0.03921  -0.0175   1.0000   0.5125
  -4.000  -0.4993   0.04687   0.04041  -0.0113   1.0000   0.5341
  -3.750  -0.4900   0.04727   0.04066  -0.0081   1.0000   0.5592
  -3.500  -0.4859   0.04792   0.04124  -0.0024   1.0000   0.5779
  -3.250  -0.4806   0.04826   0.04151   0.0025   1.0000   0.5971
  -3.000  -0.4740   0.04833   0.04149   0.0065   1.0000   0.6166
  -2.750  -0.4658   0.04817   0.04122   0.0095   1.0000   0.6358
  -2.500  -0.4564   0.04785   0.04079   0.0119   1.0000   0.6531
  -2.250  -0.4460   0.04741   0.04024   0.0138   1.0000   0.6678
  -2.000  -0.4084   0.04767   0.04027   0.0105   0.9891   0.6838
  -1.750  -0.3698   0.04762   0.03999   0.0063   0.9776   0.6958
  -1.500  -0.3284   0.04746   0.03958   0.0007   0.9656   0.7057
  -1.250  -0.2967   0.04728   0.03925  -0.0018   0.9548   0.7129
  -1.000  -0.2575   0.04719   0.03896  -0.0067   0.9439   0.7199
  -0.750  -0.2143   0.04725   0.03882  -0.0121   0.9328   0.7263
  -0.500  -0.1892   0.04700   0.03846  -0.0139   0.9223   0.7314
  -0.250  -0.1519   0.04705   0.03835  -0.0184   0.9114   0.7372
   0.000  -0.1111   0.04724   0.03840  -0.0229   0.9007   0.7426
   0.250  -0.0844   0.04727   0.03836  -0.0248   0.8903   0.7474
   0.500  -0.0503   0.04751   0.03847  -0.0284   0.8794   0.7533
   0.750  -0.0080   0.04789   0.03875  -0.0329   0.8693   0.7589
   1.000   0.0137   0.04807   0.03889  -0.0339   0.8587   0.7637
   1.250   0.0468   0.04852   0.03926  -0.0372   0.8483   0.7700
   1.500   0.0868   0.04898   0.03966  -0.0406   0.8385   0.7764
   1.750   0.1046   0.04939   0.04005  -0.0413   0.8277   0.7818
   2.000   0.1424   0.05008   0.04068  -0.0453   0.8176   0.7886
   2.250   0.1694   0.05053   0.04112  -0.0464   0.8076   0.7953
   2.500   0.1926   0.05128   0.04185  -0.0480   0.7972   0.8023
   2.750   0.2307   0.05187   0.04243  -0.0508   0.7875   0.8099
   3.000   0.2486   0.05269   0.04326  -0.0516   0.7770   0.8173
   3.250   0.2725   0.05349   0.04408  -0.0527   0.7672   0.8255
   3.500   0.3099   0.05420   0.04480  -0.0554   0.7573   0.8358
   3.750   0.3181   0.05522   0.04587  -0.0547   0.7472   0.8437
   4.000   0.3519   0.05599   0.04667  -0.0568   0.7374   0.8549
   4.250   0.3682   0.05699   0.04773  -0.0571   0.7271   0.8661
   4.500   0.3843   0.05802   0.04883  -0.0571   0.7175   0.8784
   4.750   0.4205   0.05855   0.04943  -0.0588   0.7075   0.8953
   5.000   0.4218   0.05999   0.05096  -0.0579   0.6972   0.9111
   5.250   0.4489   0.06085   0.05196  -0.0592   0.6868   0.9374
   5.500   0.4985   0.06158   0.05281  -0.0639   0.6742   1.0000
   5.750   0.5097   0.06403   0.05530  -0.0664   0.6625   1.0000
   6.000   0.5419   0.06598   0.05730  -0.0704   0.6497   1.0000
   6.250   0.5817   0.06771   0.05907  -0.0748   0.6367   1.0000
   6.500   0.6304   0.06898   0.06039  -0.0793   0.6234   1.0000
   6.750   0.6616   0.07081   0.06226  -0.0824   0.6101   1.0000
   7.000   0.6748   0.07344   0.06492  -0.0842   0.5967   1.0000
   7.250   0.6954   0.07571   0.06722  -0.0860   0.5833   1.0000
   7.500   0.7211   0.07759   0.06915  -0.0876   0.5697   1.0000
   7.750   0.7522   0.07901   0.07060  -0.0890   0.5562   1.0000
   8.000   0.7920   0.07957   0.07125  -0.0900   0.5424   1.0000
   8.250   0.8038   0.08197   0.07370  -0.0903   0.5287   1.0000
   8.500   0.8059   0.08513   0.07690  -0.0904   0.5147   1.0000
   8.750   0.8133   0.08801   0.07984  -0.0905   0.5012   1.0000
   9.000   0.8282   0.09021   0.08211  -0.0906   0.4872   1.0000
   9.250   0.8478   0.09204   0.08403  -0.0906   0.4736   1.0000
   9.500   0.8734   0.09315   0.08524  -0.0903   0.4594   1.0000
   9.750   0.9098   0.09297   0.08518  -0.0895   0.4453   1.0000
  10.000   0.9046   0.09713   0.08942  -0.0897   0.4317   1.0000
  11.000   1.3699   0.05389   0.04715  -0.0813   0.3496   1.0000
  11.250   1.2849   0.06296   0.05641  -0.0752   0.3487   1.0000
  11.500   0.9176   0.11947   0.11222  -0.0920   0.3569   1.0000
  11.750   1.3861   0.05784   0.05126  -0.0734   0.2995   1.0000
  12.000   1.3230   0.06555   0.05920  -0.0695   0.2982   1.0000
  12.250   1.2065   0.08321   0.07693  -0.0710   0.3024   1.0000
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