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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 500,000
Max Cl/Cd: 113.72 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e817-il-500000.txt
Download as CSV file: xf-e817-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4681   0.13042   0.12814  -0.0386   1.0000   0.0132
 -12.250  -0.4724   0.12769   0.12545  -0.0378   1.0000   0.0135
 -12.000  -0.4791   0.12495   0.12274  -0.0366   1.0000   0.0136
  -8.500  -0.4835   0.03032   0.02621  -0.1181   0.9580   0.0092
  -8.250  -0.4661   0.02290   0.01796  -0.1196   0.9565   0.0062
  -8.000  -0.4500   0.02135   0.01618  -0.1181   0.9522   0.0058
  -7.750  -0.4275   0.02002   0.01469  -0.1180   0.9493   0.0056
  -7.500  -0.4014   0.01857   0.01309  -0.1186   0.9475   0.0055
  -7.250  -0.3737   0.01718   0.01156  -0.1195   0.9461   0.0054
  -7.000  -0.3463   0.01543   0.00961  -0.1207   0.9447   0.0055
  -6.750  -0.3167   0.01412   0.00809  -0.1221   0.9436   0.0059
  -6.500  -0.2944   0.01325   0.00705  -0.1216   0.9406   0.0069
  -6.250  -0.2714   0.01274   0.00642  -0.1211   0.9375   0.0089
  -6.000  -0.2444   0.01162   0.00547  -0.1218   0.9355   0.0616
  -5.750  -0.2164   0.01045   0.00482  -0.1233   0.9340   0.1736
  -5.500  -0.1864   0.00979   0.00457  -0.1247   0.9328   0.2760
  -5.250  -0.1552   0.00960   0.00441  -0.1257   0.9318   0.3057
  -5.000  -0.1239   0.00947   0.00426  -0.1267   0.9309   0.3240
  -4.750  -0.0925   0.00936   0.00413  -0.1276   0.9301   0.3390
  -4.500  -0.0693   0.00938   0.00414  -0.1269   0.9274   0.3525
  -4.250  -0.0446   0.00937   0.00411  -0.1265   0.9249   0.3683
  -4.000  -0.0164   0.00933   0.00407  -0.1268   0.9230   0.3853
  -3.750   0.0130   0.00926   0.00401  -0.1274   0.9215   0.3992
  -3.500   0.0429   0.00920   0.00394  -0.1280   0.9203   0.4107
  -3.250   0.0733   0.00913   0.00388  -0.1287   0.9192   0.4220
  -3.000   0.1042   0.00906   0.00379  -0.1295   0.9182   0.4335
  -2.750   0.1351   0.00901   0.00374  -0.1303   0.9173   0.4455
  -2.500   0.1620   0.00905   0.00379  -0.1303   0.9154   0.4571
  -2.250   0.1845   0.00913   0.00391  -0.1295   0.9122   0.4679
  -2.000   0.2118   0.00913   0.00395  -0.1295   0.9101   0.4796
  -1.750   0.2411   0.00910   0.00395  -0.1300   0.9084   0.4917
  -1.500   0.2714   0.00906   0.00394  -0.1306   0.9069   0.5035
  -1.250   0.3024   0.00901   0.00392  -0.1314   0.9056   0.5160
  -1.000   0.3337   0.00896   0.00391  -0.1322   0.9044   0.5286
  -0.750   0.3629   0.00897   0.00397  -0.1326   0.9027   0.5408
  -0.500   0.3848   0.00908   0.00414  -0.1315   0.8988   0.5526
  -0.250   0.4129   0.00908   0.00418  -0.1317   0.8962   0.5652
   0.000   0.4440   0.00899   0.00416  -0.1324   0.8940   0.5780
   0.250   0.4766   0.00886   0.00411  -0.1333   0.8920   0.5907
   0.500   0.5080   0.00877   0.00409  -0.1340   0.8896   0.6035
   0.750   0.5315   0.00877   0.00417  -0.1331   0.8841   0.6158
   1.000   0.5633   0.00859   0.00406  -0.1337   0.8802   0.6288
   1.250   0.5963   0.00839   0.00392  -0.1345   0.8764   0.6420
   1.500   0.6216   0.00825   0.00390  -0.1337   0.8688   0.6549
   1.750   0.6528   0.00800   0.00370  -0.1340   0.8619   0.6682
   2.000   0.6824   0.00769   0.00343  -0.1338   0.8508   0.6816
   2.250   0.7081   0.00749   0.00331  -0.1330   0.8387   0.6948
   2.500   0.7338   0.00733   0.00322  -0.1322   0.8254   0.7083
   2.750   0.7590   0.00724   0.00323  -0.1314   0.8127   0.7219
   3.000   0.7844   0.00716   0.00328  -0.1306   0.7974   0.7359
   3.250   0.8063   0.00709   0.00327  -0.1290   0.7636   0.7502
   3.500   0.8195   0.00747   0.00320  -0.1254   0.6515   0.7645
   3.750   0.8136   0.00898   0.00381  -0.1185   0.4696   0.7795
   4.000   0.8121   0.01061   0.00453  -0.1132   0.2804   0.7953
   4.250   0.8197   0.01196   0.00519  -0.1098   0.1349   0.8124
   4.500   0.8354   0.01276   0.00571  -0.1077   0.0685   0.8316
   4.750   0.8490   0.01378   0.00648  -0.1050   0.0149   0.8525
   5.000   0.8662   0.01437   0.00721  -0.1026   0.0104   0.8775
   5.250   0.8785   0.01495   0.00799  -0.0991   0.0092   0.9139
   5.500   0.8920   0.01567   0.00888  -0.0961   0.0088   1.0000
   5.750   0.9106   0.01685   0.01021  -0.0944   0.0085   1.0000
   6.000   0.9307   0.01855   0.01204  -0.0930   0.0081   1.0000
   6.250   0.9559   0.02023   0.01384  -0.0926   0.0073   1.0000
   6.500   0.9802   0.02073   0.01440  -0.0921   0.0067   1.0000
   6.750   1.0072   0.02236   0.01618  -0.0919   0.0064   1.0000
   7.000   1.0344   0.02423   0.01822  -0.0917   0.0061   1.0000
   7.250   1.0601   0.02636   0.02058  -0.0911   0.0057   1.0000
   7.500   1.0832   0.02957   0.02414  -0.0899   0.0056   1.0000
   7.750   1.0984   0.03426   0.02933  -0.0873   0.0060   1.0000
  10.000   1.0399   0.07147   0.06908  -0.0517   0.0095   1.0000
  10.250   1.0196   0.07586   0.07362  -0.0499   0.0095   1.0000
  10.500   0.9974   0.08103   0.07893  -0.0494   0.0096   1.0000
  10.750   0.9732   0.08728   0.08533  -0.0505   0.0097   1.0000
  11.000   0.9468   0.09535   0.09353  -0.0542   0.0099   1.0000
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