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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 200,000
Max Cl/Cd: 67.27 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e818-il-200000-n5.txt
Download as CSV file: xf-e818-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4673   0.10077   0.09728  -0.0384   1.0000   0.0091
  -9.500  -0.4751   0.09728   0.09385  -0.0380   1.0000   0.0088
  -9.250  -0.4780   0.09282   0.08943  -0.0398   0.9991   0.0086
  -9.000  -0.4746   0.08682   0.08345  -0.0446   0.9967   0.0083
  -8.750  -0.4711   0.08037   0.07702  -0.0501   0.9939   0.0081
  -8.500  -0.4708   0.07261   0.06927  -0.0566   0.9900   0.0079
  -8.250  -0.4729   0.06381   0.06040  -0.0665   0.9846   0.0079
  -8.000  -0.4793   0.05714   0.05359  -0.0756   0.9769   0.0079
  -7.750  -0.4754   0.05027   0.04641  -0.0858   0.9699   0.0077
  -7.500  -0.4713   0.04552   0.04136  -0.0894   0.9632   0.0075
  -7.250  -0.4583   0.04066   0.03610  -0.0929   0.9589   0.0071
  -7.000  -0.4374   0.03608   0.03103  -0.0961   0.9565   0.0066
  -6.750  -0.4213   0.03257   0.02708  -0.0965   0.9524   0.0062
  -6.500  -0.3995   0.02932   0.02336  -0.0971   0.9491   0.0058
  -6.250  -0.3725   0.02628   0.01983  -0.0979   0.9470   0.0054
  -6.000  -0.3436   0.02393   0.01711  -0.0987   0.9455   0.0051
  -5.750  -0.3141   0.02192   0.01480  -0.0994   0.9444   0.0048
  -5.500  -0.2841   0.02030   0.01298  -0.1002   0.9435   0.0047
  -5.250  -0.2612   0.01906   0.01151  -0.0997   0.9407   0.0046
  -5.000  -0.2365   0.01795   0.01027  -0.0996   0.9378   0.0046
  -4.750  -0.2070   0.01691   0.00905  -0.1006   0.9359   0.0046
  -4.500  -0.1758   0.01609   0.00800  -0.1017   0.9344   0.0048
  -4.250  -0.1441   0.01550   0.00716  -0.1028   0.9332   0.0051
  -4.000  -0.1121   0.01507   0.00650  -0.1039   0.9322   0.0059
  -3.750  -0.0794   0.01473   0.00601  -0.1050   0.9312   0.0085
  -3.500  -0.0454   0.01280   0.00542  -0.1084   0.9308   0.3071
  -3.250  -0.0177   0.01250   0.00553  -0.1090   0.9287   0.4148
  -3.000   0.0050   0.01251   0.00543  -0.1082   0.9253   0.4301
  -2.750   0.0333   0.01248   0.00537  -0.1085   0.9232   0.4450
  -2.500   0.0635   0.01244   0.00531  -0.1092   0.9215   0.4601
  -2.250   0.0946   0.01239   0.00526  -0.1100   0.9202   0.4754
  -2.000   0.1266   0.01235   0.00522  -0.1111   0.9190   0.4908
  -1.750   0.1593   0.01230   0.00516  -0.1123   0.9180   0.5062
  -1.500   0.1923   0.01225   0.00514  -0.1135   0.9172   0.5215
  -1.250   0.2083   0.01241   0.00533  -0.1113   0.9117   0.5348
  -1.000   0.2374   0.01241   0.00538  -0.1118   0.9095   0.5500
  -0.750   0.2686   0.01238   0.00542  -0.1126   0.9078   0.5659
  -0.500   0.3009   0.01235   0.00545  -0.1137   0.9064   0.5822
  -0.250   0.3341   0.01231   0.00548  -0.1149   0.9052   0.5985
   0.000   0.3609   0.01235   0.00561  -0.1148   0.9023   0.6136
   0.250   0.3839   0.01243   0.00578  -0.1140   0.8977   0.6284
   0.500   0.4148   0.01240   0.00586  -0.1147   0.8953   0.6443
   0.750   0.4475   0.01233   0.00591  -0.1157   0.8934   0.6605
   1.000   0.4819   0.01224   0.00594  -0.1170   0.8918   0.6769
   1.250   0.5026   0.01233   0.00629  -0.1156   0.8854   0.6923
   1.500   0.5343   0.01222   0.00635  -0.1162   0.8818   0.7087
   1.750   0.5700   0.01202   0.00633  -0.1176   0.8791   0.7257
   2.000   0.5935   0.01199   0.00648  -0.1165   0.8715   0.7426
   2.250   0.6315   0.01160   0.00631  -0.1180   0.8660   0.7598
   2.500   0.6604   0.01125   0.00617  -0.1175   0.8539   0.7772
   2.750   0.6888   0.01024   0.00531  -0.1155   0.7982   0.7950
   3.000   0.6794   0.01252   0.00500  -0.1067   0.3023   0.8118
   3.250   0.6781   0.01495   0.00601  -0.1020   0.0254   0.8320
   3.500   0.6963   0.01559   0.00678  -0.0996   0.0124   0.8557
   3.750   0.7136   0.01611   0.00754  -0.0971   0.0106   0.8854
   4.000   0.7288   0.01667   0.00831  -0.0942   0.0097   0.9365
   4.250   0.7508   0.01765   0.00942  -0.0930   0.0091   1.0000
   4.500   0.7726   0.01894   0.01078  -0.0918   0.0086   1.0000
   4.750   0.7959   0.02046   0.01235  -0.0910   0.0072   1.0000
   5.000   0.8220   0.02200   0.01400  -0.0908   0.0050   1.0000
   5.250   0.8499   0.02350   0.01565  -0.0906   0.0041   1.0000
   5.500   0.8794   0.02576   0.01816  -0.0903   0.0038   1.0000
   5.750   0.9077   0.02841   0.02116  -0.0897   0.0036   1.0000
   6.000   0.9328   0.03144   0.02472  -0.0885   0.0035   1.0000
   6.250   0.9542   0.03481   0.02852  -0.0866   0.0035   1.0000
   6.500   0.9717   0.03852   0.03268  -0.0842   0.0035   1.0000
   6.750   0.9856   0.04245   0.03703  -0.0815   0.0037   1.0000
   7.000   0.9961   0.04654   0.04150  -0.0786   0.0038   1.0000
   7.250   1.0032   0.05069   0.04601  -0.0755   0.0039   1.0000
   7.500   1.0070   0.05493   0.05057  -0.0724   0.0041   1.0000
   7.750   1.0076   0.05914   0.05506  -0.0694   0.0043   1.0000
   8.000   1.0046   0.06332   0.05950  -0.0664   0.0044   1.0000
   8.250   0.9978   0.06743   0.06383  -0.0634   0.0045   1.0000
   8.500   0.9859   0.07115   0.06773  -0.0601   0.0046   1.0000
   8.750   0.9706   0.07481   0.07153  -0.0571   0.0047   1.0000
   9.000   0.9541   0.07879   0.07565  -0.0552   0.0047   1.0000
   9.250   0.9369   0.08329   0.08027  -0.0545   0.0048   1.0000
   9.500   0.9196   0.08847   0.08557  -0.0554   0.0048   1.0000
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