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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 500,000
Max Cl/Cd: 98.21 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e817-il-500000-n5.txt
Download as CSV file: xf-e817-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5052   0.08553   0.08318  -0.0627   0.9940   0.0021
 -11.500  -0.5273   0.07404   0.07158  -0.0705   0.9915   0.0021
 -11.250  -0.5375   0.06592   0.06334  -0.0774   0.9884   0.0021
 -11.000  -0.5504   0.05720   0.05445  -0.0859   0.9846   0.0021
 -10.750  -0.5548   0.05012   0.04718  -0.0942   0.9815   0.0020
 -10.500  -0.5633   0.04410   0.04096  -0.1002   0.9733   0.0020
 -10.250  -0.5669   0.03790   0.03447  -0.1078   0.9671   0.0020
 -10.000  -0.5621   0.03393   0.03025  -0.1128   0.9591   0.0020
  -9.750  -0.5552   0.02978   0.02575  -0.1176   0.9515   0.0020
  -9.500  -0.5412   0.02674   0.02238  -0.1200   0.9459   0.0020
  -9.250  -0.5233   0.02422   0.01956  -0.1215   0.9418   0.0020
  -9.000  -0.5077   0.02223   0.01730  -0.1216   0.9361   0.0020
  -8.750  -0.4875   0.02043   0.01521  -0.1221   0.9322   0.0020
  -8.500  -0.4657   0.01895   0.01353  -0.1225   0.9290   0.0020
  -8.250  -0.4473   0.01768   0.01209  -0.1220   0.9244   0.0020
  -8.000  -0.4254   0.01653   0.01077  -0.1220   0.9207   0.0021
  -7.750  -0.4013   0.01549   0.00957  -0.1223   0.9178   0.0021
  -7.500  -0.3778   0.01461   0.00855  -0.1224   0.9148   0.0021
  -7.250  -0.3549   0.01373   0.00752  -0.1223   0.9116   0.0022
  -7.000  -0.3304   0.01280   0.00639  -0.1224   0.9088   0.0026
  -6.750  -0.3035   0.01227   0.00573  -0.1227   0.9066   0.0030
  -6.500  -0.2758   0.01181   0.00518  -0.1232   0.9048   0.0041
  -6.250  -0.2479   0.01140   0.00471  -0.1236   0.9031   0.0075
  -6.000  -0.2221   0.01096   0.00427  -0.1237   0.9006   0.0214
  -5.750  -0.1963   0.01027   0.00381  -0.1241   0.8981   0.0648
  -5.500  -0.1710   0.00915   0.00323  -0.1250   0.8958   0.1833
  -5.250  -0.1431   0.00878   0.00300  -0.1255   0.8940   0.2334
  -5.000  -0.1144   0.00857   0.00283  -0.1260   0.8924   0.2606
  -4.750  -0.0854   0.00844   0.00268  -0.1265   0.8911   0.2773
  -4.500  -0.0566   0.00831   0.00256  -0.1269   0.8897   0.2954
  -4.250  -0.0290   0.00818   0.00244  -0.1271   0.8878   0.3170
  -4.000  -0.0011   0.00807   0.00237  -0.1274   0.8859   0.3364
  -3.500   0.0557   0.00792   0.00221  -0.1280   0.8823   0.3588
  -3.250   0.0844   0.00786   0.00214  -0.1283   0.8808   0.3679
  -3.000   0.1134   0.00781   0.00206  -0.1287   0.8794   0.3772
  -2.750   0.1425   0.00776   0.00201  -0.1291   0.8782   0.3872
  -2.500   0.1717   0.00771   0.00197  -0.1296   0.8769   0.3968
  -2.250   0.1993   0.00768   0.00197  -0.1297   0.8749   0.4063
  -2.000   0.2273   0.00766   0.00197  -0.1298   0.8732   0.4168
  -1.750   0.2554   0.00763   0.00197  -0.1301   0.8714   0.4270
  -1.500   0.2839   0.00760   0.00197  -0.1303   0.8695   0.4369
  -1.250   0.3126   0.00757   0.00198  -0.1306   0.8678   0.4477
  -1.000   0.3416   0.00755   0.00199  -0.1310   0.8662   0.4586
  -0.750   0.3708   0.00753   0.00200  -0.1314   0.8645   0.4692
  -0.500   0.3987   0.00751   0.00204  -0.1315   0.8622   0.4802
  -0.250   0.4260   0.00750   0.00210  -0.1315   0.8593   0.4911
   0.000   0.4541   0.00749   0.00214  -0.1316   0.8564   0.5019
   0.250   0.4829   0.00745   0.00217  -0.1319   0.8532   0.5130
   0.500   0.5118   0.00742   0.00219  -0.1321   0.8496   0.5247
   0.750   0.5381   0.00739   0.00224  -0.1318   0.8440   0.5362
   1.000   0.5667   0.00733   0.00224  -0.1319   0.8387   0.5480
   1.250   0.5932   0.00730   0.00228  -0.1316   0.8316   0.5596
   1.500   0.6211   0.00723   0.00229  -0.1315   0.8232   0.5716
   1.750   0.6473   0.00718   0.00230  -0.1310   0.8116   0.5835
   2.000   0.6719   0.00712   0.00230  -0.1302   0.7921   0.5956
   2.250   0.6963   0.00709   0.00227  -0.1292   0.7612   0.6076
   2.500   0.7132   0.00741   0.00222  -0.1266   0.6682   0.6194
   2.750   0.7205   0.00833   0.00259  -0.1224   0.5494   0.6303
   3.000   0.7329   0.00910   0.00299  -0.1194   0.4568   0.6420
   3.250   0.7474   0.00986   0.00344  -0.1170   0.3683   0.6539
   3.500   0.7609   0.01077   0.00391  -0.1145   0.2609   0.6661
   3.750   0.7776   0.01156   0.00436  -0.1127   0.1756   0.6790
   4.000   0.7940   0.01242   0.00485  -0.1108   0.0921   0.6921
   4.250   0.8130   0.01310   0.00530  -0.1094   0.0430   0.7059
   4.500   0.8348   0.01355   0.00570  -0.1084   0.0241   0.7203
   4.750   0.8563   0.01403   0.00616  -0.1073   0.0100   0.7352
   5.000   0.8782   0.01449   0.00670  -0.1061   0.0058   0.7504
   5.250   0.8999   0.01495   0.00727  -0.1050   0.0048   0.7661
   5.500   0.9211   0.01547   0.00791  -0.1037   0.0044   0.7819
   5.750   0.9411   0.01607   0.00872  -0.1022   0.0041   0.7988
   6.000   0.9596   0.01678   0.00959  -0.1004   0.0039   0.8179
   6.250   0.9754   0.01775   0.01074  -0.0981   0.0036   0.8394
   6.500   0.9912   0.01858   0.01174  -0.0958   0.0033   0.8659
   6.750   1.0054   0.01891   0.01222  -0.0931   0.0031   0.9074
   7.000   1.0224   0.01940   0.01284  -0.0910   0.0028   1.0000
   7.250   1.0433   0.02026   0.01378  -0.0900   0.0026   1.0000
   7.500   1.0641   0.02139   0.01504  -0.0889   0.0025   1.0000
   7.750   1.0854   0.02256   0.01633  -0.0879   0.0024   1.0000
   8.000   1.1066   0.02375   0.01767  -0.0870   0.0022   1.0000
   8.250   1.1272   0.02496   0.01901  -0.0860   0.0020   1.0000
   8.500   1.1467   0.02622   0.02042  -0.0849   0.0019   1.0000
   8.750   1.1646   0.02750   0.02190  -0.0835   0.0018   1.0000
   9.000   1.1807   0.02884   0.02339  -0.0819   0.0017   1.0000
   9.250   1.1946   0.03044   0.02519  -0.0800   0.0016   1.0000
   9.500   1.2049   0.03258   0.02758  -0.0776   0.0015   1.0000
   9.750   1.2068   0.03588   0.03128  -0.0741   0.0014   1.0000
  10.000   1.1960   0.04043   0.03633  -0.0692   0.0014   1.0000
  10.250   1.1829   0.04450   0.04078  -0.0644   0.0013   1.0000
  10.500   1.1628   0.04915   0.04582  -0.0597   0.0013   1.0000
  10.750   1.1463   0.05327   0.05023  -0.0562   0.0013   1.0000
  11.000   1.1276   0.05778   0.05499  -0.0533   0.0013   1.0000
  11.250   1.1088   0.06251   0.05995  -0.0515   0.0013   1.0000
  11.500   1.0874   0.06796   0.06561  -0.0507   0.0013   1.0000
  11.750   1.0658   0.07401   0.07184  -0.0513   0.0013   1.0000
  12.000   1.0503   0.07973   0.07771  -0.0531   0.0014   1.0000
  12.250   1.0321   0.08703   0.08516  -0.0568   0.0014   1.0000
  12.500   1.0133   0.09672   0.09499  -0.0631   0.0014   1.0000
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