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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 200,000
Max Cl/Cd: 71.35 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e817-il-200000-n5.txt
Download as CSV file: xf-e817-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 817 HYDROFOIL 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5363   0.08600   0.08258  -0.0519   0.9986   0.0048
 -10.750  -0.5470   0.07674   0.07323  -0.0595   0.9960   0.0047
 -10.500  -0.5585   0.06787   0.06422  -0.0679   0.9928   0.0047
 -10.250  -0.5710   0.05983   0.05599  -0.0760   0.9879   0.0046
 -10.000  -0.5749   0.05363   0.04959  -0.0836   0.9833   0.0046
  -9.750  -0.5827   0.04805   0.04376  -0.0897   0.9764   0.0046
  -9.500  -0.5862   0.04354   0.03897  -0.0949   0.9698   0.0045
  -9.250  -0.5889   0.03998   0.03512  -0.0970   0.9619   0.0045
  -9.000  -0.5799   0.03620   0.03093  -0.0995   0.9577   0.0045
  -8.750  -0.5675   0.03315   0.02750  -0.1006   0.9539   0.0046
  -8.500  -0.5560   0.03079   0.02476  -0.1002   0.9489   0.0046
  -8.250  -0.5365   0.02840   0.02205  -0.1009   0.9463   0.0047
  -8.000  -0.5133   0.02629   0.01966  -0.1017   0.9445   0.0048
  -7.750  -0.4880   0.02447   0.01760  -0.1028   0.9432   0.0049
  -7.500  -0.4745   0.02330   0.01626  -0.1011   0.9388   0.0051
  -7.250  -0.4552   0.02149   0.01425  -0.1011   0.9356   0.0054
  -7.000  -0.4298   0.01990   0.01246  -0.1021   0.9336   0.0066
  -6.750  -0.4008   0.01896   0.01136  -0.1033   0.9322   0.0079
  -6.500  -0.3709   0.01816   0.01043  -0.1047   0.9311   0.0121
  -6.250  -0.3402   0.01696   0.00917  -0.1062   0.9302   0.0257
  -6.000  -0.3216   0.01609   0.00851  -0.1055   0.9268   0.0663
  -5.750  -0.2985   0.01496   0.00778  -0.1061   0.9241   0.1467
  -5.500  -0.2704   0.01425   0.00732  -0.1071   0.9223   0.2365
  -5.250  -0.2404   0.01398   0.00707  -0.1081   0.9209   0.2776
  -5.000  -0.2098   0.01381   0.00685  -0.1090   0.9197   0.3038
  -4.750  -0.1788   0.01366   0.00667  -0.1099   0.9188   0.3266
  -4.500  -0.1474   0.01355   0.00652  -0.1110   0.9179   0.3514
  -4.250  -0.1156   0.01346   0.00639  -0.1121   0.9171   0.3732
  -4.000  -0.0949   0.01348   0.00638  -0.1109   0.9137   0.3846
  -3.750  -0.0715   0.01347   0.00630  -0.1102   0.9108   0.3947
  -3.500  -0.0437   0.01344   0.00621  -0.1104   0.9091   0.4053
  -3.250  -0.0137   0.01339   0.00612  -0.1111   0.9076   0.4166
  -3.000   0.0173   0.01332   0.00603  -0.1119   0.9064   0.4275
  -2.750   0.0486   0.01326   0.00597  -0.1129   0.9054   0.4388
  -2.500   0.0801   0.01321   0.00588  -0.1138   0.9045   0.4504
  -2.250   0.1124   0.01315   0.00583  -0.1149   0.9036   0.4620
  -2.000   0.1265   0.01335   0.00604  -0.1124   0.8984   0.4721
  -1.750   0.1537   0.01337   0.00608  -0.1125   0.8961   0.4841
  -1.500   0.1836   0.01336   0.00608  -0.1131   0.8944   0.4959
  -1.250   0.2149   0.01333   0.00609  -0.1139   0.8930   0.5083
  -1.000   0.2468   0.01329   0.00610  -0.1149   0.8919   0.5210
  -0.750   0.2795   0.01325   0.00610  -0.1160   0.8908   0.5336
  -0.500   0.2969   0.01344   0.00636  -0.1141   0.8858   0.5449
  -0.250   0.3234   0.01349   0.00648  -0.1140   0.8829   0.5574
   0.000   0.3539   0.01347   0.00653  -0.1146   0.8809   0.5704
   0.250   0.3862   0.01342   0.00656  -0.1156   0.8793   0.5839
   0.500   0.4197   0.01335   0.00658  -0.1167   0.8779   0.5976
   1.000   0.4676   0.01350   0.00695  -0.1153   0.8690   0.6235
   1.250   0.5010   0.01337   0.00694  -0.1163   0.8666   0.6377
   1.500   0.5367   0.01319   0.00689  -0.1178   0.8647   0.6522
   1.750   0.5568   0.01327   0.00714  -0.1162   0.8576   0.6655
   2.000   0.5910   0.01303   0.00703  -0.1172   0.8535   0.6801
   2.250   0.6231   0.01279   0.00694  -0.1176   0.8481   0.6946
   2.500   0.6542   0.01245   0.00675  -0.1178   0.8396   0.7095
   2.750   0.6833   0.01204   0.00648  -0.1173   0.8270   0.7245
   3.000   0.7091   0.01158   0.00614  -0.1160   0.8068   0.7396
   3.250   0.7315   0.01128   0.00603  -0.1142   0.7810   0.7550
   3.500   0.7539   0.01102   0.00587  -0.1124   0.7410   0.7707
   3.750   0.7884   0.01105   0.00516  -0.1123   0.5824   0.7861
   4.000   0.7928   0.01210   0.00563  -0.1075   0.4604   0.8030
   4.250   0.7947   0.01328   0.00624  -0.1027   0.3386   0.8218
   4.500   0.7985   0.01449   0.00689  -0.0984   0.2181   0.8430
   4.750   0.8072   0.01547   0.00749  -0.0950   0.1313   0.8687
   5.000   0.8162   0.01626   0.00803  -0.0916   0.0764   0.9063
   5.250   0.8316   0.01694   0.00856  -0.0894   0.0409   1.0000
   5.500   0.8508   0.01784   0.00930  -0.0882   0.0188   1.0000
   5.750   0.8704   0.01878   0.01029  -0.0868   0.0120   1.0000
   6.000   0.8903   0.01968   0.01137  -0.0855   0.0099   1.0000
   6.250   0.9084   0.02085   0.01264  -0.0839   0.0086   1.0000
   6.500   0.9254   0.02246   0.01437  -0.0821   0.0079   1.0000
   6.750   0.9469   0.02439   0.01643  -0.0811   0.0075   1.0000
   7.000   0.9737   0.02615   0.01835  -0.0810   0.0073   1.0000
   7.250   1.0025   0.02827   0.02069  -0.0812   0.0072   1.0000
   7.500   1.0295   0.03068   0.02338  -0.0810   0.0071   1.0000
   7.750   1.0530   0.03338   0.02642  -0.0803   0.0070   1.0000
   8.000   1.0720   0.03612   0.02954  -0.0788   0.0068   1.0000
   8.250   1.0879   0.03834   0.03208  -0.0770   0.0063   1.0000
   8.500   1.1011   0.04049   0.03454  -0.0749   0.0056   1.0000
   8.750   1.1112   0.04261   0.03694  -0.0726   0.0050   1.0000
   9.000   1.1179   0.04476   0.03934  -0.0700   0.0046   1.0000
   9.250   1.1173   0.04767   0.04257  -0.0663   0.0045   1.0000
   9.500   1.1110   0.05095   0.04617  -0.0622   0.0044   1.0000
   9.750   1.1011   0.05432   0.04983  -0.0581   0.0044   1.0000
  10.000   1.0878   0.05797   0.05384  -0.0543   0.0043   1.0000
  10.250   1.0713   0.06210   0.05823  -0.0511   0.0043   1.0000
  10.500   1.0531   0.06650   0.06287  -0.0486   0.0043   1.0000
  10.750   1.0309   0.07185   0.06839  -0.0471   0.0044   1.0000
  11.000   1.0068   0.07793   0.07470  -0.0470   0.0044   1.0000
  11.250   0.9810   0.08508   0.08204  -0.0487   0.0045   1.0000
  11.500   0.9549   0.09371   0.09084  -0.0529   0.0047   1.0000
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