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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 200,000
Max Cl/Cd: 79.86 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e817-il-200000.txt
Download as CSV file: xf-e817-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5902   0.08779   0.08461  -0.0506   1.0000   0.0439
  -9.250  -0.6143   0.08449   0.08129  -0.0510   1.0000   0.0439
  -9.000  -0.6418   0.08189   0.07868  -0.0502   1.0000   0.0439
  -8.750  -0.6678   0.07934   0.07609  -0.0497   1.0000   0.0438
  -8.500  -0.6863   0.07610   0.07273  -0.0499   1.0000   0.0439
  -8.250  -0.7077   0.06646   0.06305  -0.0527   0.9991   0.0451
  -8.000  -0.6971   0.06195   0.05857  -0.0538   0.9974   0.0462
  -7.750  -0.6908   0.05759   0.05407  -0.0560   0.9954   0.0472
  -7.500  -0.6834   0.04408   0.03943  -0.0590   0.9932   0.0184
  -7.250  -0.6684   0.03900   0.03387  -0.0608   0.9910   0.0169
  -7.000  -0.6481   0.03416   0.02842  -0.0619   0.9896   0.0155
  -6.750  -0.6235   0.03051   0.02423  -0.0626   0.9885   0.0144
  -6.500  -0.5964   0.02775   0.02108  -0.0632   0.9871   0.0140
  -6.250  -0.5678   0.02566   0.01872  -0.0638   0.9856   0.0140
  -6.000  -0.5385   0.02392   0.01680  -0.0647   0.9843   0.0149
  -5.750  -0.5083   0.02250   0.01524  -0.0658   0.9832   0.0163
  -5.500  -0.4752   0.02174   0.01435  -0.0674   0.9819   0.0209
  -5.250  -0.4399   0.01961   0.01212  -0.0702   0.9808   0.0423
  -5.000  -0.4057   0.01689   0.01068  -0.0742   0.9798   0.2826
  -4.750  -0.3797   0.01685   0.01058  -0.0743   0.9778   0.3302
  -4.500  -0.3519   0.01692   0.01056  -0.0747   0.9756   0.3572
  -4.250  -0.3225   0.01706   0.01059  -0.0754   0.9735   0.3803
  -4.000  -0.2921   0.01720   0.01068  -0.0763   0.9716   0.3993
  -3.750  -0.2593   0.01745   0.01087  -0.0776   0.9698   0.4205
  -3.500  -0.2292   0.01769   0.01106  -0.0784   0.9677   0.4413
  -3.250  -0.2059   0.01767   0.01100  -0.0778   0.9646   0.4560
  -3.000  -0.1781   0.01772   0.01098  -0.0782   0.9620   0.4687
  -2.750  -0.1477   0.01782   0.01105  -0.0791   0.9596   0.4817
  -2.500  -0.1142   0.01798   0.01118  -0.0805   0.9574   0.4956
  -2.000  -0.0599   0.01816   0.01137  -0.0810   0.9513   0.5221
  -1.750  -0.0313   0.01828   0.01146  -0.0815   0.9481   0.5363
  -1.500   0.0018   0.01844   0.01163  -0.0828   0.9454   0.5512
  -1.250   0.0375   0.01867   0.01190  -0.0847   0.9434   0.5662
  -1.000   0.0587   0.01873   0.01200  -0.0837   0.9385   0.5798
  -0.750   0.0877   0.01885   0.01218  -0.0843   0.9347   0.5942
  -0.500   0.1223   0.01902   0.01240  -0.0858   0.9319   0.6100
  -0.250   0.1607   0.01926   0.01269  -0.0881   0.9298   0.6261
   0.000   0.1776   0.01930   0.01280  -0.0863   0.9229   0.6401
   0.250   0.2121   0.01943   0.01300  -0.0878   0.9194   0.6569
   0.500   0.2511   0.01959   0.01324  -0.0900   0.9170   0.6739
   0.750   0.2697   0.01968   0.01342  -0.0885   0.9096   0.6888
   1.000   0.3049   0.01975   0.01361  -0.0900   0.9060   0.7056
   1.250   0.3452   0.01983   0.01380  -0.0924   0.9036   0.7238
   1.500   0.3638   0.01991   0.01401  -0.0908   0.8951   0.7407
   1.750   0.4029   0.01985   0.01409  -0.0928   0.8918   0.7586
   2.000   0.4271   0.01987   0.01425  -0.0920   0.8840   0.7771
   2.250   0.4646   0.01969   0.01422  -0.0936   0.8795   0.7968
   2.500   0.5093   0.01937   0.01411  -0.0962   0.8769   0.8172
   2.750   0.5306   0.01918   0.01408  -0.0946   0.8668   0.8387
   3.000   0.5840   0.01828   0.01339  -0.0982   0.8638   0.8617
   3.250   0.6119   0.01754   0.01284  -0.0970   0.8528   0.8886
   3.500   0.6632   0.01567   0.01118  -0.0990   0.8418   0.9168
   3.750   0.7187   0.01376   0.00956  -0.1019   0.8297   0.9550
   4.000   0.7740   0.01214   0.00812  -0.1054   0.8121   1.0000
   4.250   0.8025   0.01146   0.00754  -0.1046   0.7829   1.0000
   4.500   0.8433   0.01056   0.00605  -0.1047   0.6160   1.0000
   4.750   0.8348   0.01257   0.00666  -0.0979   0.3868   1.0000
   5.000   0.8271   0.01488   0.00770  -0.0923   0.1746   1.0000
   5.250   0.8321   0.01697   0.00892  -0.0889   0.0612   1.0000
   5.500   0.8439   0.01875   0.01051  -0.0861   0.0275   1.0000
   5.750   0.8607   0.02023   0.01208  -0.0839   0.0227   1.0000
   6.000   0.8824   0.02173   0.01364  -0.0827   0.0203   1.0000
   6.250   0.9114   0.02359   0.01565  -0.0828   0.0190   1.0000
   6.500   0.9469   0.02597   0.01817  -0.0838   0.0186   1.0000
   6.750   0.9848   0.02907   0.02157  -0.0848   0.0191   1.0000
   7.000   1.0180   0.03330   0.02633  -0.0845   0.0208   1.0000
   7.250   1.0404   0.03800   0.03154  -0.0827   0.0233   1.0000
   7.500   1.0539   0.04270   0.03665  -0.0803   0.0249   1.0000
   7.750   1.0617   0.04804   0.04234  -0.0776   0.0258   1.0000
  11.750   0.8742   0.13356   0.13081  -0.0735   0.0349   1.0000
  12.000   0.8707   0.14024   0.13746  -0.0776   0.0341   1.0000
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