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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.56 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e818-il-1000000.txt
Download as CSV file: xf-e818-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4173   0.07933   0.07775  -0.0642   0.9916   0.0060
  -9.000  -0.4145   0.07215   0.07057  -0.0705   0.9887   0.0060
  -8.750  -0.4202   0.05703   0.05537  -0.0866   0.9849   0.0053
  -8.500  -0.4222   0.04716   0.04529  -0.1032   0.9787   0.0051
  -8.250  -0.4127   0.04156   0.03945  -0.1126   0.9721   0.0053
  -8.000  -0.3933   0.03705   0.03469  -0.1190   0.9699   0.0056
  -7.750  -0.3750   0.03349   0.03088  -0.1223   0.9660   0.0062
  -7.500  -0.3554   0.03038   0.02751  -0.1242   0.9611   0.0069
  -7.250  -0.3301   0.02772   0.02460  -0.1261   0.9582   0.0080
  -7.000  -0.2959   0.02830   0.02510  -0.1268   0.9568   0.0100
  -6.750  -0.2724   0.02704   0.02358  -0.1272   0.9523   0.0103
  -6.500  -0.2578   0.02056   0.01649  -0.1281   0.9465   0.0112
  -6.250  -0.2327   0.01756   0.01327  -0.1292   0.9437   0.0132
  -6.000  -0.2078   0.01617   0.01173  -0.1292   0.9402   0.0151
  -5.750  -0.1816   0.01493   0.01035  -0.1292   0.9367   0.0177
  -5.500  -0.1513   0.01575   0.01106  -0.1293   0.9340   0.0215
  -5.000  -0.0988   0.01015   0.00517  -0.1280   0.9284   0.0079
  -4.750  -0.0712   0.00895   0.00372  -0.1280   0.9253   0.0052
  -4.500  -0.0425   0.00854   0.00321  -0.1283   0.9228   0.0043
  -4.250  -0.0136   0.00819   0.00276  -0.1286   0.9206   0.0039
  -4.000   0.0160   0.00785   0.00226  -0.1290   0.9186   0.0037
  -3.750   0.0451   0.00769   0.00197  -0.1293   0.9165   0.0037
  -3.500   0.0731   0.00758   0.00180  -0.1294   0.9142   0.0038
  -3.250   0.1014   0.00672   0.00143  -0.1304   0.9119   0.1580
  -3.000   0.1300   0.00620   0.00129  -0.1312   0.9099   0.2656
  -2.750   0.1588   0.00596   0.00125  -0.1317   0.9079   0.3195
  -2.500   0.1877   0.00564   0.00126  -0.1324   0.9061   0.4138
  -2.250   0.2169   0.00559   0.00125  -0.1329   0.9043   0.4400
  -2.000   0.2449   0.00555   0.00125  -0.1331   0.9023   0.4530
  -1.250   0.3303   0.00545   0.00125  -0.1339   0.8954   0.4930
  -0.500   0.4152   0.00537   0.00130  -0.1345   0.8866   0.5327
  -0.250   0.4434   0.00534   0.00130  -0.1346   0.8828   0.5458
   0.000   0.4722   0.00531   0.00130  -0.1348   0.8788   0.5593
   0.250   0.4994   0.00528   0.00133  -0.1348   0.8741   0.5728
   0.500   0.5271   0.00522   0.00131  -0.1347   0.8674   0.5864
   0.750   0.5550   0.00521   0.00142  -0.1347   0.8627   0.6004
   1.000   0.5816   0.00514   0.00139  -0.1343   0.8509   0.6142
   1.250   0.6075   0.00509   0.00138  -0.1338   0.8363   0.6279
   1.500   0.6331   0.00506   0.00139  -0.1332   0.8178   0.6417
   1.750   0.6543   0.00517   0.00134  -0.1315   0.7550   0.6552
   2.000   0.6529   0.00679   0.00181  -0.1255   0.4948   0.6671
   2.250   0.6480   0.00955   0.00275  -0.1198   0.0699   0.6789
   2.500   0.6700   0.01024   0.00333  -0.1185   0.0066   0.6931
   2.750   0.6942   0.01070   0.00400  -0.1176   0.0061   0.7076
   3.000   0.7202   0.01088   0.00421  -0.1173   0.0051   0.7231
   3.250   0.7446   0.01128   0.00473  -0.1166   0.0045   0.7388
   3.500   0.7687   0.01172   0.00526  -0.1158   0.0039   0.7553
   3.750   0.7924   0.01219   0.00581  -0.1150   0.0031   0.7720
   4.000   0.8118   0.01331   0.00709  -0.1131   0.0024   0.7890
   4.250   0.8309   0.01508   0.00905  -0.1110   0.0022   0.8064
   4.500   0.8552   0.01654   0.01067  -0.1100   0.0022   0.8247
   4.750   0.8807   0.01760   0.01189  -0.1092   0.0024   0.8448
   5.250   0.9248   0.01510   0.01040  -0.1031   0.0038   0.8509
   5.500   0.9443   0.01731   0.01291  -0.1011   0.0035   0.8706
   5.750   0.9605   0.02006   0.01604  -0.0984   0.0033   0.8923
   6.000   0.9721   0.02252   0.01881  -0.0951   0.0031   0.9252
   6.250   0.9798   0.02542   0.02199  -0.0911   0.0030   1.0000
   6.500   0.9921   0.02904   0.02587  -0.0886   0.0029   1.0000
   6.750   1.0017   0.03306   0.03013  -0.0858   0.0028   1.0000
   7.000   1.0091   0.03705   0.03433  -0.0831   0.0027   1.0000
   7.250   1.0136   0.04132   0.03882  -0.0803   0.0026   1.0000
   7.500   1.0145   0.04593   0.04364  -0.0772   0.0026   1.0000
   7.750   1.0115   0.05078   0.04868  -0.0739   0.0025   1.0000
   8.000   1.0046   0.05540   0.05348  -0.0706   0.0025   1.0000
   8.250   0.9918   0.05966   0.05788  -0.0668   0.0025   1.0000
   8.500   0.9711   0.06338   0.06172  -0.0622   0.0025   1.0000
   8.750   0.9491   0.06761   0.06608  -0.0589   0.0025   1.0000
   9.000   0.9245   0.07296   0.07156  -0.0569   0.0025   1.0000
   9.250   0.8988   0.07902   0.07773  -0.0566   0.0026   1.0000
   9.500   0.8703   0.08686   0.08569  -0.0585   0.0026   1.0000
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