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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 200,000
Max Cl/Cd: 77.19 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e668-il-200000-n5.txt
Download as CSV file: xf-e668-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1388   0.09190   0.08763  -0.1178   0.8992   0.0102
 -11.250  -0.1389   0.08693   0.08266  -0.1206   0.8966   0.0101
 -10.750  -0.2409   0.05414   0.04979  -0.1379   0.8866   0.0086
 -10.500  -0.2664   0.04658   0.04199  -0.1444   0.8823   0.0085
 -10.250  -0.2786   0.04327   0.03855  -0.1456   0.8787   0.0084
 -10.000  -0.3043   0.03933   0.03435  -0.1449   0.8740   0.0084
  -9.750  -0.3234   0.03666   0.03141  -0.1423   0.8697   0.0084
  -9.500  -0.3287   0.03467   0.02917  -0.1402   0.8669   0.0084
  -9.250  -0.3334   0.03206   0.02618  -0.1379   0.8643   0.0085
  -9.000  -0.3324   0.02961   0.02330  -0.1356   0.8614   0.0086
  -8.750  -0.3226   0.02797   0.02142  -0.1341   0.8587   0.0088
  -8.500  -0.3080   0.02685   0.02016  -0.1331   0.8565   0.0092
  -8.250  -0.2915   0.02562   0.01872  -0.1321   0.8546   0.0095
  -8.000  -0.2734   0.02439   0.01726  -0.1313   0.8529   0.0098
  -7.750  -0.2537   0.02322   0.01586  -0.1305   0.8513   0.0103
  -7.500  -0.2330   0.02226   0.01469  -0.1298   0.8496   0.0115
  -7.250  -0.2135   0.02175   0.01413  -0.1290   0.8474   0.0123
  -7.000  -0.1931   0.02108   0.01330  -0.1281   0.8454   0.0138
  -6.750  -0.1727   0.02041   0.01259  -0.1274   0.8434   0.0149
  -6.500  -0.1513   0.01974   0.01183  -0.1267   0.8413   0.0164
  -6.250  -0.1293   0.01905   0.01105  -0.1260   0.8393   0.0181
  -6.000  -0.1055   0.01857   0.01049  -0.1257   0.8377   0.0214
  -5.750  -0.0811   0.01809   0.00994  -0.1254   0.8363   0.0254
  -5.500  -0.0560   0.01760   0.00940  -0.1253   0.8349   0.0308
  -5.250  -0.0341   0.01723   0.00904  -0.1246   0.8327   0.0377
  -5.000  -0.0131   0.01691   0.00876  -0.1238   0.8300   0.0472
  -4.750   0.0098   0.01660   0.00847  -0.1233   0.8278   0.0612
  -4.500   0.0338   0.01625   0.00820  -0.1230   0.8256   0.0821
  -4.250   0.0591   0.01592   0.00794  -0.1229   0.8236   0.1114
  -4.000   0.0852   0.01555   0.00771  -0.1230   0.8219   0.1517
  -3.750   0.1119   0.01518   0.00750  -0.1233   0.8205   0.2056
  -3.500   0.1393   0.01480   0.00732  -0.1237   0.8191   0.2704
  -3.250   0.1585   0.01462   0.00738  -0.1226   0.8155   0.3343
  -3.000   0.1808   0.01436   0.00739  -0.1221   0.8124   0.4084
  -2.750   0.2053   0.01406   0.00737  -0.1218   0.8098   0.4906
  -2.500   0.2304   0.01380   0.00740  -0.1213   0.8077   0.5763
  -2.250   0.2560   0.01370   0.00751  -0.1206   0.8059   0.6471
  -2.000   0.2823   0.01375   0.00763  -0.1199   0.8043   0.6941
  -1.750   0.3029   0.01398   0.00789  -0.1183   0.8010   0.7251
  -1.500   0.3227   0.01423   0.00814  -0.1167   0.7967   0.7482
  -1.250   0.3475   0.01437   0.00824  -0.1160   0.7938   0.7666
  -1.000   0.3749   0.01443   0.00824  -0.1158   0.7915   0.7816
  -0.750   0.4042   0.01446   0.00820  -0.1159   0.7896   0.7949
  -0.500   0.4332   0.01447   0.00816  -0.1159   0.7879   0.8057
  -0.250   0.4450   0.01480   0.00853  -0.1129   0.7813   0.8154
   0.000   0.4707   0.01485   0.00855  -0.1125   0.7779   0.8257
   0.250   0.4965   0.01481   0.00849  -0.1118   0.7753   0.8330
   0.500   0.5270   0.01473   0.00837  -0.1122   0.7733   0.8418
   0.750   0.5411   0.01493   0.00860  -0.1095   0.7675   0.8494
   1.000   0.5639   0.01496   0.00863  -0.1086   0.7630   0.8574
   1.250   0.5898   0.01483   0.00850  -0.1079   0.7600   0.8636
   1.500   0.6213   0.01465   0.00830  -0.1085   0.7577   0.8703
   1.750   0.6312   0.01484   0.00855  -0.1051   0.7499   0.8769
   2.000   0.6575   0.01469   0.00841  -0.1047   0.7459   0.8825
   2.250   0.6901   0.01446   0.00817  -0.1056   0.7431   0.8872
   2.500   0.6999   0.01460   0.00837  -0.1022   0.7348   0.8928
   2.750   0.7276   0.01439   0.00818  -0.1021   0.7305   0.8972
   3.000   0.7501   0.01435   0.00816  -0.1012   0.7243   0.9021
   3.500   0.7944   0.01408   0.00797  -0.0989   0.7113   0.9111
   4.000   0.8330   0.01394   0.00791  -0.0957   0.6942   0.9215
   4.250   0.8597   0.01374   0.00774  -0.0954   0.6858   0.9262
   4.500   0.8792   0.01370   0.00774  -0.0938   0.6748   0.9321
   4.750   0.9041   0.01355   0.00760  -0.0932   0.6636   0.9376
   5.000   0.9315   0.01340   0.00746  -0.0930   0.6505   0.9431
   5.250   0.9578   0.01332   0.00738  -0.0927   0.6353   0.9493
   5.500   0.9846   0.01329   0.00733  -0.0926   0.6168   0.9569
   5.750   1.0136   0.01331   0.00730  -0.0929   0.5954   0.9653
   6.250   1.0622   0.01376   0.00756  -0.0923   0.5447   1.0000
   6.500   1.0804   0.01420   0.00791  -0.0910   0.5183   1.0000
   6.750   1.0962   0.01474   0.00834  -0.0894   0.4918   1.0000
   7.000   1.1100   0.01537   0.00885  -0.0875   0.4654   1.0000
   7.250   1.1222   0.01607   0.00945  -0.0854   0.4389   1.0000
   7.500   1.1336   0.01684   0.01013  -0.0834   0.4124   1.0000
   7.750   1.1440   0.01769   0.01087  -0.0813   0.3868   1.0000
   8.000   1.1546   0.01857   0.01166  -0.0792   0.3618   1.0000
   8.250   1.1649   0.01950   0.01251  -0.0773   0.3375   1.0000
   8.500   1.1749   0.02048   0.01341  -0.0753   0.3138   1.0000
   8.750   1.1853   0.02148   0.01434  -0.0735   0.2905   1.0000
   9.000   1.1946   0.02257   0.01534  -0.0717   0.2672   1.0000
   9.250   1.2050   0.02364   0.01635  -0.0700   0.2452   1.0000
   9.500   1.2144   0.02480   0.01742  -0.0682   0.2231   1.0000
   9.750   1.2238   0.02599   0.01855  -0.0666   0.2020   1.0000
  10.000   1.2336   0.02719   0.01969  -0.0650   0.1819   1.0000
  10.250   1.2429   0.02845   0.02090  -0.0635   0.1637   1.0000
  10.500   1.2520   0.02976   0.02215  -0.0620   0.1467   1.0000
  10.750   1.2617   0.03105   0.02342  -0.0606   0.1312   1.0000
  11.000   1.2708   0.03241   0.02476  -0.0592   0.1166   1.0000
  11.250   1.2798   0.03383   0.02616  -0.0579   0.1036   1.0000
  11.500   1.2881   0.03532   0.02764  -0.0566   0.0918   1.0000
  11.750   1.2965   0.03685   0.02916  -0.0553   0.0815   1.0000
  12.000   1.3052   0.03837   0.03073  -0.0542   0.0726   1.0000
  12.250   1.3132   0.04000   0.03240  -0.0530   0.0651   1.0000
  12.500   1.3197   0.04181   0.03423  -0.0519   0.0584   1.0000
  12.750   1.3273   0.04356   0.03605  -0.0509   0.0526   1.0000
  13.000   1.3332   0.04550   0.03805  -0.0499   0.0476   1.0000
  13.250   1.3388   0.04754   0.04015  -0.0490   0.0431   1.0000
  13.500   1.3438   0.04969   0.04238  -0.0481   0.0395   1.0000
  13.750   1.3484   0.05194   0.04472  -0.0474   0.0361   1.0000
  14.000   1.3514   0.05442   0.04728  -0.0467   0.0334   1.0000
  14.250   1.3554   0.05686   0.04984  -0.0462   0.0307   1.0000
  14.500   1.3562   0.05973   0.05278  -0.0458   0.0288   1.0000
  14.750   1.3590   0.06246   0.05564  -0.0455   0.0267   1.0000
  15.000   1.3608   0.06536   0.05866  -0.0453   0.0248   1.0000
  15.500   1.3602   0.07197   0.06551  -0.0455   0.0219   1.0000
  15.750   1.3603   0.07534   0.06901  -0.0459   0.0205   1.0000
  16.000   1.3575   0.07920   0.07296  -0.0465   0.0194   1.0000
  16.250   1.3555   0.08304   0.07696  -0.0471   0.0183   1.0000
  16.500   1.3537   0.08695   0.08102  -0.0480   0.0173   1.0000
  16.750   1.3507   0.09113   0.08533  -0.0491   0.0163   1.0000
  17.000   1.3446   0.09588   0.09019  -0.0506   0.0156   1.0000
  17.250   1.3406   0.10040   0.09487  -0.0521   0.0149   1.0000
  17.500   1.3362   0.10508   0.09972  -0.0538   0.0141   1.0000
  17.750   1.3310   0.10998   0.10477  -0.0558   0.0134   1.0000
  18.000   1.3247   0.11517   0.11008  -0.0581   0.0129   1.0000
  18.250   1.3167   0.12073   0.11574  -0.0607   0.0125   1.0000
  18.500   1.3115   0.12587   0.12107  -0.0632   0.0119   1.0000
  18.750   1.3054   0.13123   0.12660  -0.0660   0.0113   1.0000
  19.000   1.2988   0.13681   0.13232  -0.0690   0.0108   1.0000
  19.250   1.2918   0.14255   0.13819  -0.0724   0.0104   1.0000
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