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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 500,000
Max Cl/Cd: 104.16 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e818-il-500000.txt
Download as CSV file: xf-e818-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 818 HYDROFOIL 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4612   0.11690   0.11463  -0.0367   1.0000   0.0109
 -10.750  -0.4669   0.11308   0.11084  -0.0366   1.0000   0.0112
 -10.500  -0.4731   0.10977   0.10757  -0.0360   1.0000   0.0114
 -10.250  -0.4798   0.10676   0.10459  -0.0352   1.0000   0.0116
 -10.000  -0.4872   0.10415   0.10202  -0.0340   1.0000   0.0119
  -9.750  -0.4808   0.09956   0.09742  -0.0374   0.9989   0.0121
  -9.500  -0.4729   0.09493   0.09280  -0.0412   0.9975   0.0125
  -9.250  -0.4656   0.08983   0.08771  -0.0457   0.9957   0.0129
  -9.000  -0.4585   0.08436   0.08225  -0.0509   0.9941   0.0133
  -8.750  -0.4539   0.07859   0.07648  -0.0562   0.9916   0.0136
  -8.500  -0.4531   0.06981   0.06772  -0.0644   0.9878   0.0134
  -8.250  -0.4589   0.05655   0.05428  -0.0834   0.9823   0.0128
  -8.000  -0.4580   0.05024   0.04776  -0.0936   0.9738   0.0129
  -7.750  -0.4446   0.04505   0.04232  -0.1005   0.9704   0.0134
  -5.250  -0.1978   0.01687   0.01115  -0.1141   0.9469   0.0108
  -5.000  -0.1667   0.01441   0.00859  -0.1151   0.9461   0.0084
  -4.750  -0.1327   0.01293   0.00694  -0.1167   0.9454   0.0073
  -4.500  -0.0979   0.01192   0.00572  -0.1184   0.9448   0.0066
  -4.250  -0.0638   0.01133   0.00494  -0.1199   0.9442   0.0064
  -4.000  -0.0301   0.01099   0.00443  -0.1212   0.9436   0.0067
  -3.750  -0.0046   0.01087   0.00418  -0.1208   0.9410   0.0081
  -3.500   0.0209   0.00967   0.00372  -0.1215   0.9381   0.2048
  -3.250   0.0508   0.00912   0.00356  -0.1227   0.9365   0.3240
  -3.000   0.0815   0.00897   0.00349  -0.1236   0.9352   0.3589
  -2.750   0.1131   0.00872   0.00351  -0.1248   0.9341   0.4297
  -2.500   0.1451   0.00861   0.00353  -0.1259   0.9331   0.4726
  -2.250   0.1775   0.00853   0.00348  -0.1270   0.9321   0.4878
  -2.000   0.2100   0.00846   0.00341  -0.1282   0.9312   0.5029
  -1.750   0.2425   0.00840   0.00337  -0.1293   0.9304   0.5178
  -1.500   0.2630   0.00850   0.00352  -0.1280   0.9262   0.5312
  -1.250   0.2908   0.00850   0.00356  -0.1282   0.9238   0.5459
  -1.000   0.3212   0.00845   0.00357  -0.1288   0.9220   0.5602
  -0.750   0.3529   0.00838   0.00356  -0.1298   0.9206   0.5749
  -0.500   0.3854   0.00829   0.00352  -0.1308   0.9192   0.5898
  -0.250   0.4182   0.00820   0.00350  -0.1319   0.9178   0.6047
   0.000   0.4426   0.00826   0.00362  -0.1313   0.9140   0.6192
   0.250   0.4708   0.00821   0.00365  -0.1314   0.9103   0.6341
   0.500   0.5029   0.00807   0.00360  -0.1323   0.9075   0.6495
   0.750   0.5365   0.00791   0.00359  -0.1333   0.9050   0.6649
   1.000   0.5619   0.00787   0.00366  -0.1327   0.8991   0.6793
   1.250   0.5931   0.00766   0.00356  -0.1332   0.8938   0.6942
   1.500   0.6214   0.00741   0.00340  -0.1328   0.8839   0.7092
   1.750   0.6509   0.00699   0.00302  -0.1322   0.8664   0.7243
   2.000   0.6742   0.00669   0.00275  -0.1304   0.8374   0.7395
   2.250   0.6906   0.00663   0.00242  -0.1270   0.7342   0.7550
   2.500   0.6701   0.00951   0.00328  -0.1174   0.3135   0.7696
   2.750   0.6735   0.01184   0.00432  -0.1131   0.0137   0.7853
   3.000   0.6968   0.01227   0.00496  -0.1119   0.0115   0.8032
   3.250   0.7187   0.01287   0.00574  -0.1104   0.0110   0.8225
   3.500   0.7401   0.01336   0.00634  -0.1090   0.0088   0.8428
   3.750   0.7547   0.01473   0.00789  -0.1062   0.0065   0.8655
   4.000   0.7720   0.01563   0.00895  -0.1037   0.0059   0.8930
   4.250   0.7855   0.01626   0.00974  -0.1003   0.0054   0.9418
   4.500   0.8120   0.01787   0.01148  -0.0996   0.0051   1.0000
   4.750   0.8428   0.02044   0.01424  -0.0994   0.0053   1.0000
   5.000   0.8735   0.02273   0.01665  -0.0992   0.0070   1.0000
   5.500   0.9203   0.03497   0.02997  -0.0943   0.0147   1.0000
   5.750   0.9497   0.03396   0.02910  -0.0932   0.0121   1.0000
   6.000   0.9690   0.03658   0.03201  -0.0911   0.0107   1.0000
   6.250   0.9854   0.03946   0.03523  -0.0889   0.0096   1.0000
   6.500   0.9990   0.04245   0.03847  -0.0867   0.0088   1.0000
   6.750   1.0103   0.04545   0.04170  -0.0844   0.0082   1.0000
   7.000   1.0192   0.04847   0.04491  -0.0822   0.0078   1.0000
   7.250   1.0252   0.05170   0.04833  -0.0799   0.0074   1.0000
   7.500   1.0263   0.05551   0.05235  -0.0771   0.0070   1.0000
   7.750   1.0217   0.05997   0.05703  -0.0741   0.0068   1.0000
   8.000   1.0108   0.06504   0.06233  -0.0707   0.0066   1.0000
   8.250   0.9951   0.07020   0.06768  -0.0672   0.0064   1.0000
   8.500   0.9761   0.07417   0.07180  -0.0632   0.0064   1.0000
   8.750   0.9576   0.07792   0.07568  -0.0602   0.0063   1.0000
   9.000   0.9404   0.08189   0.07977  -0.0585   0.0063   1.0000
   9.250   0.9254   0.08606   0.08405  -0.0580   0.0063   1.0000
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