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EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 654 AIRFOIL (e654-il)
Reynolds number: 200,000
Max Cl/Cd: 70.6 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e654-il-200000.txt
Download as CSV file: xf-e654-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 654 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0167   0.10312   0.09883  -0.1235   0.8514   0.0524
 -11.500  -0.0161   0.09969   0.09538  -0.1255   0.8461   0.0549
 -11.250  -0.0455   0.09274   0.08846  -0.1323   0.8414   0.0568
 -11.000  -0.0255   0.09099   0.08669  -0.1305   0.8370   0.0576
 -10.750  -0.0160   0.08860   0.08429  -0.1308   0.8326   0.0582
 -10.500  -0.0059   0.08638   0.08205  -0.1310   0.8287   0.0601
 -10.250  -0.0043   0.08306   0.07870  -0.1326   0.8252   0.0616
 -10.000  -0.0703   0.07166   0.06738  -0.1455   0.8200   0.0654
  -9.750  -0.1079   0.06719   0.06284  -0.1485   0.8147   0.0654
  -9.500  -0.0538   0.06537   0.06115  -0.1452   0.8129   0.0670
  -9.250  -0.1885   0.04758   0.04269  -0.1483   0.8069   0.0371
  -9.000  -0.2121   0.04207   0.03681  -0.1457   0.8029   0.0301
  -8.750  -0.2452   0.03658   0.03037  -0.1414   0.7986   0.0266
  -8.500  -0.2354   0.03419   0.02775  -0.1402   0.7956   0.0263
  -8.250  -0.2229   0.03203   0.02528  -0.1391   0.7928   0.0262
  -8.000  -0.2077   0.03003   0.02291  -0.1381   0.7904   0.0262
  -7.750  -0.1906   0.02837   0.02091  -0.1370   0.7876   0.0264
  -7.500  -0.1723   0.02692   0.01923  -0.1360   0.7844   0.0268
  -7.250  -0.1512   0.02570   0.01802  -0.1355   0.7815   0.0278
  -7.000  -0.1289   0.02485   0.01710  -0.1349   0.7789   0.0291
  -6.750  -0.1062   0.02404   0.01608  -0.1343   0.7765   0.0316
  -6.500  -0.0827   0.02335   0.01542  -0.1340   0.7744   0.0344
  -6.250  -0.0587   0.02249   0.01444  -0.1335   0.7723   0.0370
  -6.000  -0.0383   0.02192   0.01393  -0.1326   0.7696   0.0407
  -5.750  -0.0190   0.02143   0.01350  -0.1317   0.7665   0.0462
  -5.500   0.0015   0.02091   0.01302  -0.1309   0.7638   0.0542
  -5.250   0.0230   0.02032   0.01247  -0.1303   0.7613   0.0665
  -5.000   0.0462   0.01980   0.01203  -0.1301   0.7589   0.0857
  -4.750   0.0707   0.01918   0.01154  -0.1300   0.7568   0.1156
  -4.500   0.0959   0.01853   0.01115  -0.1303   0.7549   0.1680
  -4.250   0.1172   0.01812   0.01110  -0.1302   0.7523   0.2458
  -4.000   0.1368   0.01780   0.01122  -0.1300   0.7491   0.3397
  -3.750   0.1592   0.01746   0.01134  -0.1298   0.7462   0.4502
  -3.500   0.1828   0.01735   0.01164  -0.1291   0.7436   0.5548
  -3.250   0.2085   0.01757   0.01197  -0.1283   0.7414   0.6193
  -3.000   0.2351   0.01790   0.01226  -0.1277   0.7395   0.6564
  -2.750   0.2631   0.01828   0.01254  -0.1273   0.7379   0.6842
  -2.500   0.2858   0.01885   0.01308  -0.1261   0.7357   0.7029
  -2.250   0.2968   0.01971   0.01400  -0.1233   0.7308   0.7170
  -2.000   0.3151   0.02027   0.01456  -0.1213   0.7274   0.7302
  -1.750   0.3376   0.02067   0.01492  -0.1199   0.7251   0.7433
  -1.500   0.3649   0.02090   0.01505  -0.1196   0.7232   0.7565
  -1.250   0.3890   0.02111   0.01522  -0.1181   0.7214   0.7659
  -1.000   0.4161   0.02130   0.01534  -0.1175   0.7199   0.7767
  -0.750   0.4102   0.02268   0.01684  -0.1127   0.7125   0.7864
  -0.500   0.4271   0.02306   0.01721  -0.1107   0.7090   0.7954
  -0.250   0.4542   0.02318   0.01726  -0.1104   0.7069   0.8060
   0.000   0.4787   0.02315   0.01720  -0.1091   0.7052   0.8136
   0.250   0.5112   0.02311   0.01707  -0.1098   0.7037   0.8233
   0.500   0.5373   0.02307   0.01699  -0.1088   0.7023   0.8297
   0.750   0.5137   0.02508   0.01914  -0.1023   0.6911   0.8395
   1.000   0.5397   0.02490   0.01893  -0.1014   0.6892   0.8457
   1.250   0.5732   0.02465   0.01862  -0.1021   0.6879   0.8525
   1.500   0.6090   0.02436   0.01826  -0.1032   0.6867   0.8584
   1.750   0.6407   0.02412   0.01798  -0.1035   0.6855   0.8636
   2.000   0.6108   0.02636   0.02036  -0.0963   0.6728   0.8729
   2.250   0.6440   0.02590   0.01987  -0.0966   0.6715   0.8774
   2.500   0.6110   0.02823   0.02229  -0.0890   0.6592   0.8868
   2.750   0.6423   0.02789   0.02194  -0.0893   0.6571   0.8915
   3.000   0.6808   0.02731   0.02134  -0.0906   0.6560   0.8959
   3.250   0.7244   0.02671   0.02070  -0.0929   0.6551   0.9001
   3.500   0.7698   0.02604   0.02000  -0.0956   0.6543   0.9039
   3.750   0.8080   0.02539   0.01933  -0.0968   0.6533   0.9078
   4.000   0.8497   0.02475   0.01867  -0.0987   0.6523   0.9117
   4.250   0.8104   0.02681   0.02086  -0.0895   0.6390   0.9231
   4.500   0.7946   0.02844   0.02257  -0.0841   0.6289   0.9339
   4.750   0.8534   0.02681   0.02091  -0.0878   0.6308   0.9366
   5.000   0.9177   0.02531   0.01939  -0.0928   0.6325   0.9388
   5.250   0.9888   0.02363   0.01764  -0.0989   0.6348   0.9402
   5.500   0.9591   0.02510   0.01926  -0.0908   0.6226   0.9566
   5.750   1.0106   0.02411   0.01828  -0.0943   0.6216   0.9613
   6.000   1.0625   0.02310   0.01727  -0.0979   0.6203   0.9668
   6.250   1.1148   0.02221   0.01637  -0.1018   0.6187   0.9725
   6.500   1.1117   0.02333   0.01765  -0.0986   0.6076   1.0000
   6.750   1.1663   0.02226   0.01657  -0.1027   0.6056   1.0000
   7.000   1.2207   0.02124   0.01553  -0.1069   0.6034   1.0000
   7.250   1.2192   0.02207   0.01650  -0.1034   0.5930   1.0000
   7.500   1.2714   0.02107   0.01550  -0.1072   0.5895   1.0000
   7.750   1.2868   0.02126   0.01577  -0.1059   0.5815   1.0000
   8.000   1.3219   0.02077   0.01530  -0.1072   0.5752   1.0000
   8.250   1.3479   0.02060   0.01519  -0.1073   0.5678   1.0000
   8.500   1.3727   0.02042   0.01504  -0.1071   0.5593   1.0000
   8.750   1.3851   0.02070   0.01538  -0.1052   0.5491   1.0000
   9.000   1.4218   0.02014   0.01479  -0.1066   0.5405   1.0000
   9.250   1.4259   0.02074   0.01545  -0.1036   0.5277   1.0000
   9.500   1.4347   0.02131   0.01605  -0.1013   0.5144   1.0000
   9.750   1.4464   0.02184   0.01657  -0.0996   0.5002   1.0000
  10.000   1.4579   0.02245   0.01717  -0.0978   0.4849   1.0000
  10.250   1.4676   0.02322   0.01790  -0.0959   0.4687   1.0000
  10.500   1.4755   0.02415   0.01877  -0.0939   0.4515   1.0000
  10.750   1.4824   0.02522   0.01977  -0.0919   0.4341   1.0000
  11.000   1.4876   0.02646   0.02092  -0.0898   0.4165   1.0000
  11.500   1.4923   0.02949   0.02383  -0.0856   0.3820   1.0000
  11.750   1.4933   0.03121   0.02550  -0.0835   0.3653   1.0000
  12.000   1.4937   0.03303   0.02727  -0.0816   0.3490   1.0000
  12.250   1.4941   0.03492   0.02913  -0.0797   0.3332   1.0000
  12.500   1.4946   0.03689   0.03104  -0.0780   0.3179   1.0000
  13.000   1.4948   0.04112   0.03521  -0.0750   0.2884   1.0000
  13.250   1.4953   0.04334   0.03743  -0.0737   0.2741   1.0000
  13.500   1.4958   0.04563   0.03971  -0.0725   0.2603   1.0000
  13.750   1.4964   0.04798   0.04206  -0.0714   0.2470   1.0000
  14.000   1.4972   0.05039   0.04445  -0.0705   0.2343   1.0000
  14.250   1.4974   0.05290   0.04693  -0.0696   0.2223   1.0000
  14.500   1.4973   0.05551   0.04951  -0.0688   0.2105   1.0000
  14.750   1.4983   0.05814   0.05219  -0.0682   0.1987   1.0000
  15.000   1.4989   0.06086   0.05492  -0.0677   0.1877   1.0000
  15.250   1.4988   0.06368   0.05771  -0.0672   0.1775   1.0000
  15.500   1.4980   0.06666   0.06070  -0.0668   0.1674   1.0000
  15.750   1.4989   0.06954   0.06365  -0.0666   0.1575   1.0000
  16.000   1.4980   0.07265   0.06674  -0.0664   0.1487   1.0000
  16.250   1.4971   0.07585   0.06996  -0.0663   0.1400   1.0000
  16.500   1.4973   0.07899   0.07316  -0.0664   0.1316   1.0000
  16.750   1.4951   0.08237   0.07647  -0.0665   0.1243   1.0000
  17.000   1.4953   0.08568   0.07993  -0.0668   0.1166   1.0000
  17.250   1.4933   0.08917   0.08340  -0.0671   0.1101   1.0000
  17.500   1.4925   0.09269   0.08702  -0.0676   0.1034   1.0000
  17.750   1.4909   0.09621   0.09053  -0.0681   0.0976   1.0000
  18.000   1.4893   0.09990   0.09433  -0.0688   0.0918   1.0000
  18.250   1.4880   0.10344   0.09784  -0.0695   0.0866   1.0000
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