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EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.08 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e836-il-1000000.txt
Download as CSV file: xf-e836-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E836 HYDROFOIL AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7576   0.08894   0.08721  -0.0264   1.0000   0.0046
 -13.750  -0.7811   0.07843   0.07657  -0.0336   1.0000   0.0044
 -13.500  -0.8115   0.06851   0.06647  -0.0400   1.0000   0.0043
 -13.250  -0.8353   0.06143   0.05923  -0.0437   1.0000   0.0043
 -13.000  -0.8599   0.05523   0.05284  -0.0459   1.0000   0.0043
 -12.750  -0.8935   0.04861   0.04598  -0.0467   1.0000   0.0042
 -12.500  -0.9173   0.04373   0.04086  -0.0460   1.0000   0.0041
 -12.250  -0.9259   0.04091   0.03788  -0.0449   1.0000   0.0043
 -12.000  -0.9388   0.03767   0.03443  -0.0430   1.0000   0.0043
 -11.750  -0.9595   0.03348   0.02990  -0.0397   1.0000   0.0042
 -11.500  -0.9580   0.03189   0.02817  -0.0377   1.0000   0.0044
 -11.250  -0.9539   0.03060   0.02676  -0.0357   1.0000   0.0046
 -11.000  -0.9560   0.02826   0.02418  -0.0327   1.0000   0.0046
 -10.750  -0.9513   0.02670   0.02246  -0.0302   1.0000   0.0047
 -10.500  -0.9424   0.02580   0.02146  -0.0279   1.0000   0.0050
 -10.250  -0.9342   0.02463   0.02015  -0.0254   1.0000   0.0051
 -10.000  -0.9248   0.02361   0.01901  -0.0229   1.0000   0.0052
  -9.750  -0.9143   0.02256   0.01785  -0.0204   1.0000   0.0052
  -9.500  -0.8984   0.02147   0.01664  -0.0190   0.9969   0.0053
  -9.250  -0.8691   0.01944   0.01441  -0.0208   0.9788   0.0054
  -9.000  -0.8417   0.01736   0.01214  -0.0221   0.9590   0.0056
  -8.750  -0.8249   0.01608   0.01066  -0.0209   0.9327   0.0059
  -8.500  -0.8094   0.01548   0.00993  -0.0189   0.9151   0.0062
  -8.250  -0.7923   0.01493   0.00929  -0.0173   0.9028   0.0064
  -8.000  -0.7728   0.01451   0.00880  -0.0161   0.8935   0.0068
  -7.750  -0.7541   0.01401   0.00820  -0.0146   0.8852   0.0073
  -7.500  -0.7346   0.01347   0.00758  -0.0133   0.8778   0.0078
  -7.000  -0.6958   0.01233   0.00623  -0.0107   0.8651   0.0092
  -6.750  -0.6748   0.01188   0.00572  -0.0096   0.8596   0.0106
  -6.500  -0.6513   0.01158   0.00539  -0.0090   0.8547   0.0123
  -6.250  -0.6297   0.01109   0.00484  -0.0080   0.8495   0.0157
  -6.000  -0.6062   0.01080   0.00450  -0.0074   0.8449   0.0188
  -5.750  -0.5831   0.01043   0.00414  -0.0067   0.8405   0.0261
  -5.500  -0.5609   0.00997   0.00378  -0.0059   0.8360   0.0482
  -5.250  -0.5395   0.00949   0.00345  -0.0050   0.8316   0.0850
  -5.000  -0.5181   0.00898   0.00314  -0.0042   0.8275   0.1327
  -4.750  -0.4972   0.00841   0.00284  -0.0033   0.8233   0.1961
  -4.500  -0.4759   0.00787   0.00256  -0.0024   0.8192   0.2618
  -4.250  -0.4546   0.00736   0.00230  -0.0015   0.8153   0.3319
  -4.000  -0.4342   0.00673   0.00202  -0.0005   0.8114   0.4231
  -3.750  -0.4134   0.00616   0.00179   0.0005   0.8074   0.5113
  -3.500  -0.3895   0.00586   0.00166   0.0011   0.8037   0.5690
  -3.250  -0.3643   0.00568   0.00159   0.0015   0.8002   0.6114
  -3.000  -0.3376   0.00557   0.00154   0.0017   0.7966   0.6387
  -2.750  -0.3102   0.00551   0.00149   0.0017   0.7929   0.6587
  -2.500  -0.2825   0.00548   0.00145   0.0016   0.7894   0.6724
  -2.250  -0.2546   0.00546   0.00142   0.0015   0.7860   0.6827
  -2.000  -0.2264   0.00543   0.00139   0.0014   0.7822   0.6923
  -1.750  -0.1981   0.00543   0.00137   0.0012   0.7785   0.7022
  -1.500  -0.1701   0.00541   0.00136   0.0011   0.7749   0.7101
  -1.250  -0.1416   0.00543   0.00133   0.0009   0.7713   0.7171
  -1.000  -0.1133   0.00541   0.00133   0.0007   0.7673   0.7236
  -0.750  -0.0848   0.00542   0.00132   0.0005   0.7631   0.7306
  -0.250  -0.0283   0.00542   0.00132   0.0002   0.7533   0.7427
   0.000   0.0000   0.00540   0.00131   0.0000   0.7479   0.7479
   0.250   0.0282   0.00542   0.00132  -0.0001   0.7427   0.7533
   0.750   0.0847   0.00542   0.00132  -0.0005   0.7306   0.7631
   1.000   0.1132   0.00541   0.00133  -0.0007   0.7236   0.7672
   1.250   0.1415   0.00543   0.00133  -0.0008   0.7171   0.7713
   1.500   0.1700   0.00541   0.00136  -0.0011   0.7101   0.7749
   1.750   0.1980   0.00543   0.00137  -0.0012   0.7023   0.7785
   2.000   0.2263   0.00543   0.00139  -0.0013   0.6923   0.7822
   2.250   0.2545   0.00546   0.00142  -0.0015   0.6827   0.7860
   2.500   0.2824   0.00548   0.00145  -0.0016   0.6724   0.7894
   2.750   0.3101   0.00551   0.00149  -0.0016   0.6586   0.7929
   3.000   0.3374   0.00557   0.00154  -0.0016   0.6387   0.7966
   3.250   0.3641   0.00568   0.00159  -0.0015   0.6114   0.8002
   3.500   0.3894   0.00586   0.00166  -0.0011   0.5688   0.8037
   3.750   0.4132   0.00616   0.00179  -0.0005   0.5114   0.8074
   4.000   0.4341   0.00672   0.00202   0.0005   0.4239   0.8114
   4.250   0.4543   0.00737   0.00230   0.0016   0.3306   0.8153
   4.500   0.4756   0.00787   0.00256   0.0025   0.2606   0.8192
   4.750   0.4968   0.00842   0.00284   0.0034   0.1944   0.8233
   5.000   0.5174   0.00901   0.00315   0.0043   0.1299   0.8276
   5.250   0.5391   0.00949   0.00345   0.0051   0.0850   0.8317
   5.500   0.5606   0.00996   0.00378   0.0060   0.0487   0.8360
   5.750   0.5827   0.01043   0.00414   0.0068   0.0259   0.8405
   6.000   0.6058   0.01080   0.00451   0.0075   0.0188   0.8449
   6.250   0.6291   0.01110   0.00484   0.0081   0.0155   0.8495
   6.500   0.6509   0.01157   0.00538   0.0091   0.0123   0.8547
   6.750   0.6740   0.01190   0.00575   0.0098   0.0108   0.8596
   7.000   0.6947   0.01238   0.00628   0.0109   0.0090   0.8652
   7.500   0.7342   0.01345   0.00757   0.0134   0.0077   0.8779
   7.750   0.7537   0.01399   0.00818   0.0147   0.0072   0.8854
   8.000   0.7723   0.01450   0.00879   0.0162   0.0069   0.8936
   8.250   0.7919   0.01491   0.00927   0.0174   0.0065   0.9030
   8.500   0.8089   0.01546   0.00992   0.0191   0.0062   0.9154
   8.750   0.8243   0.01607   0.01064   0.0210   0.0059   0.9333
   9.000   0.8411   0.01742   0.01220   0.0223   0.0056   0.9596
   9.250   0.8693   0.01937   0.01434   0.0207   0.0054   0.9793
   9.500   0.8984   0.02143   0.01660   0.0191   0.0053   0.9974
   9.750   0.9147   0.02220   0.01746   0.0205   0.0052   1.0000
  10.000   0.9257   0.02298   0.01834   0.0229   0.0051   1.0000
  10.250   0.9345   0.02432   0.01981   0.0254   0.0050   1.0000
  10.500   0.9430   0.02551   0.02115   0.0279   0.0049   1.0000
  10.750   0.9448   0.02778   0.02364   0.0309   0.0050   1.0000
  11.000   0.9519   0.02881   0.02479   0.0332   0.0048   1.0000
  11.250   0.9604   0.02956   0.02562   0.0351   0.0044   1.0000
  11.500   0.9565   0.03202   0.02831   0.0379   0.0044   1.0000
  11.750   0.9442   0.03528   0.03185   0.0410   0.0045   1.0000
  12.000   0.9419   0.03725   0.03399   0.0429   0.0043   1.0000
  12.250   0.9258   0.04089   0.03786   0.0450   0.0044   1.0000
  12.500   0.9109   0.04448   0.04166   0.0463   0.0043   1.0000
  12.750   0.8923   0.04872   0.04610   0.0468   0.0042   1.0000
  13.000   0.8561   0.05572   0.05336   0.0459   0.0044   1.0000
  13.250   0.8357   0.06133   0.05912   0.0438   0.0044   1.0000
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