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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 500,000
Max Cl/Cd: 102.6 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e68-il-500000-n5.txt
Download as CSV file: xf-e68-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6325   0.08450   0.08171  -0.0639   1.0000   0.0081
 -13.750  -0.6752   0.07338   0.07043  -0.0696   1.0000   0.0080
 -13.500  -0.7125   0.06392   0.06079  -0.0744   1.0000   0.0079
 -13.250  -0.7391   0.05693   0.05367  -0.0778   1.0000   0.0078
 -13.000  -0.7573   0.05053   0.04711  -0.0822   0.9994   0.0078
 -12.750  -0.7571   0.04439   0.04080  -0.0899   0.9966   0.0079
 -12.500  -0.7516   0.03962   0.03583  -0.0965   0.9932   0.0080
 -12.250  -0.7464   0.03557   0.03158  -0.1016   0.9883   0.0080
 -12.000  -0.7350   0.03235   0.02818  -0.1063   0.9843   0.0082
 -11.750  -0.7271   0.03019   0.02587  -0.1078   0.9771   0.0082
 -11.500  -0.7131   0.02810   0.02361  -0.1096   0.9722   0.0084
 -11.250  -0.7006   0.02651   0.02186  -0.1095   0.9651   0.0085
 -11.000  -0.6805   0.02496   0.02015  -0.1106   0.9610   0.0087
 -10.750  -0.6560   0.02349   0.01852  -0.1121   0.9586   0.0088
 -10.500  -0.6384   0.02239   0.01729  -0.1117   0.9519   0.0091
 -10.250  -0.6138   0.02124   0.01599  -0.1126   0.9481   0.0093
 -10.000  -0.5864   0.02012   0.01472  -0.1139   0.9453   0.0095
  -9.750  -0.5645   0.01922   0.01371  -0.1137   0.9395   0.0097
  -9.500  -0.5388   0.01835   0.01272  -0.1143   0.9350   0.0099
  -9.250  -0.5104   0.01751   0.01176  -0.1153   0.9315   0.0101
  -9.000  -0.4862   0.01683   0.01097  -0.1153   0.9261   0.0103
  -8.750  -0.4621   0.01596   0.01000  -0.1154   0.9205   0.0106
  -8.500  -0.4350   0.01516   0.00911  -0.1160   0.9163   0.0110
  -8.250  -0.4119   0.01461   0.00849  -0.1155   0.9100   0.0115
  -8.000  -0.3856   0.01412   0.00792  -0.1156   0.9047   0.0120
  -7.750  -0.3587   0.01366   0.00738  -0.1158   0.9000   0.0127
  -7.500  -0.3343   0.01325   0.00689  -0.1155   0.8938   0.0133
  -7.250  -0.3076   0.01285   0.00639  -0.1155   0.8887   0.0138
  -7.000  -0.2825   0.01239   0.00587  -0.1153   0.8832   0.0148
  -6.750  -0.2570   0.01202   0.00546  -0.1150   0.8773   0.0161
  -6.500  -0.2298   0.01170   0.00505  -0.1151   0.8724   0.0179
  -6.250  -0.2048   0.01135   0.00470  -0.1147   0.8664   0.0218
  -6.000  -0.1788   0.01102   0.00436  -0.1146   0.8607   0.0304
  -5.750  -0.1524   0.01069   0.00406  -0.1145   0.8555   0.0424
  -5.500  -0.1267   0.01040   0.00380  -0.1143   0.8493   0.0543
  -5.250  -0.0998   0.01016   0.00356  -0.1142   0.8438   0.0665
  -5.000  -0.0735   0.00993   0.00335  -0.1141   0.8380   0.0796
  -4.750  -0.0470   0.00969   0.00315  -0.1140   0.8319   0.0973
  -4.500  -0.0202   0.00944   0.00295  -0.1140   0.8264   0.1194
  -4.250   0.0059   0.00920   0.00278  -0.1138   0.8201   0.1447
  -4.000   0.0329   0.00900   0.00262  -0.1138   0.8143   0.1696
  -3.750   0.0595   0.00880   0.00248  -0.1137   0.8081   0.1939
  -3.500   0.0865   0.00865   0.00235  -0.1136   0.8017   0.2165
  -3.250   0.1135   0.00849   0.00224  -0.1136   0.7958   0.2424
  -3.000   0.1402   0.00831   0.00214  -0.1134   0.7889   0.2748
  -2.750   0.1673   0.00816   0.00204  -0.1134   0.7828   0.3057
  -2.000   0.2481   0.00780   0.00185  -0.1131   0.7620   0.3951
  -1.750   0.2752   0.00772   0.00180  -0.1130   0.7552   0.4243
  -1.500   0.3022   0.00763   0.00178  -0.1129   0.7478   0.4522
  -1.250   0.3292   0.00758   0.00175  -0.1128   0.7406   0.4784
  -1.000   0.3562   0.00753   0.00175  -0.1126   0.7332   0.5040
  -0.750   0.3831   0.00749   0.00174  -0.1125   0.7257   0.5290
  -0.500   0.4101   0.00745   0.00175  -0.1123   0.7180   0.5524
   0.000   0.4637   0.00742   0.00179  -0.1119   0.7020   0.5976
   0.250   0.4902   0.00742   0.00182  -0.1116   0.6940   0.6201
   0.500   0.5168   0.00742   0.00186  -0.1114   0.6852   0.6419
   0.750   0.5431   0.00743   0.00190  -0.1111   0.6765   0.6638
   1.000   0.5691   0.00747   0.00196  -0.1107   0.6669   0.6856
   1.250   0.5951   0.00749   0.00202  -0.1103   0.6568   0.7066
   1.500   0.6207   0.00753   0.00209  -0.1098   0.6467   0.7273
   2.000   0.6715   0.00765   0.00226  -0.1087   0.6253   0.7653
   2.250   0.6964   0.00772   0.00235  -0.1081   0.6139   0.7831
   2.500   0.7208   0.00780   0.00245  -0.1073   0.6018   0.8002
   2.750   0.7448   0.00790   0.00256  -0.1065   0.5891   0.8172
   3.000   0.7683   0.00801   0.00267  -0.1056   0.5762   0.8340
   3.250   0.7916   0.00812   0.00279  -0.1046   0.5633   0.8508
   3.500   0.8141   0.00824   0.00292  -0.1035   0.5491   0.8672
   3.750   0.8359   0.00837   0.00305  -0.1022   0.5342   0.8844
   4.250   0.8761   0.00866   0.00332  -0.0989   0.5017   0.9230
   4.500   0.8978   0.00881   0.00347  -0.0976   0.4841   0.9480
   4.750   0.9285   0.00905   0.00364  -0.0985   0.4620   0.9883
   5.000   0.9503   0.00933   0.00384  -0.0974   0.4403   1.0000
   5.250   0.9710   0.00964   0.00406  -0.0962   0.4174   1.0000
   5.500   0.9912   0.00997   0.00431  -0.0949   0.3942   1.0000
   5.750   1.0103   0.01035   0.00458  -0.0934   0.3700   1.0000
   6.000   1.0277   0.01074   0.00486  -0.0916   0.3431   1.0000
   6.250   1.0436   0.01121   0.00519  -0.0896   0.3139   1.0000
   6.500   1.0587   0.01172   0.00557  -0.0874   0.2841   1.0000
   6.750   1.0742   0.01224   0.00597  -0.0854   0.2560   1.0000
   7.000   1.0890   0.01281   0.00640  -0.0832   0.2275   1.0000
   7.250   1.1038   0.01340   0.00685  -0.0812   0.2004   1.0000
   7.500   1.1189   0.01397   0.00732  -0.0792   0.1781   1.0000
   7.750   1.1322   0.01465   0.00786  -0.0770   0.1516   1.0000
   8.000   1.1457   0.01532   0.00842  -0.0749   0.1284   1.0000
   8.250   1.1590   0.01602   0.00901  -0.0728   0.1075   1.0000
   8.500   1.1719   0.01674   0.00963  -0.0707   0.0893   1.0000
   8.750   1.1863   0.01739   0.01024  -0.0688   0.0770   1.0000
   9.000   1.2003   0.01807   0.01088  -0.0670   0.0659   1.0000
   9.250   1.2144   0.01875   0.01155  -0.0652   0.0569   1.0000
   9.500   1.2277   0.01950   0.01227  -0.0634   0.0485   1.0000
   9.750   1.2403   0.02031   0.01306  -0.0615   0.0403   1.0000
  10.250   1.2635   0.02209   0.01481  -0.0578   0.0261   1.0000
  10.500   1.2748   0.02304   0.01575  -0.0559   0.0208   1.0000
  10.750   1.2852   0.02407   0.01680  -0.0541   0.0166   1.0000
  11.000   1.2958   0.02512   0.01788  -0.0524   0.0144   1.0000
  11.250   1.3071   0.02614   0.01895  -0.0508   0.0131   1.0000
  11.500   1.3170   0.02729   0.02014  -0.0492   0.0119   1.0000
  11.750   1.3261   0.02853   0.02144  -0.0475   0.0112   1.0000
  12.000   1.3358   0.02976   0.02275  -0.0461   0.0106   1.0000
  12.250   1.3453   0.03103   0.02409  -0.0447   0.0101   1.0000
  12.500   1.3541   0.03239   0.02553  -0.0433   0.0097   1.0000
  12.750   1.3618   0.03387   0.02710  -0.0420   0.0093   1.0000
  13.000   1.3682   0.03551   0.02881  -0.0407   0.0088   1.0000
  13.250   1.3731   0.03734   0.03072  -0.0394   0.0084   1.0000
  13.500   1.3757   0.03945   0.03292  -0.0382   0.0081   1.0000
  13.750   1.3811   0.04136   0.03492  -0.0372   0.0079   1.0000
  14.000   1.3854   0.04344   0.03710  -0.0364   0.0078   1.0000
  14.250   1.3896   0.04558   0.03935  -0.0356   0.0076   1.0000
  14.500   1.3922   0.04798   0.04185  -0.0350   0.0074   1.0000
  14.750   1.3943   0.05052   0.04449  -0.0345   0.0072   1.0000
  15.000   1.3963   0.05314   0.04722  -0.0342   0.0071   1.0000
  15.250   1.3961   0.05611   0.05031  -0.0340   0.0070   1.0000
  15.500   1.3969   0.05907   0.05337  -0.0341   0.0068   1.0000
  15.750   1.3957   0.06238   0.05679  -0.0343   0.0066   1.0000
  16.000   1.3958   0.06559   0.06010  -0.0346   0.0064   1.0000
  16.250   1.3936   0.06922   0.06383  -0.0352   0.0063   1.0000
  16.500   1.3898   0.07320   0.06792  -0.0360   0.0062   1.0000
  16.750   1.3833   0.07772   0.07257  -0.0371   0.0061   1.0000
  17.000   1.3769   0.08233   0.07728  -0.0385   0.0059   1.0000
  17.250   1.3692   0.08729   0.08237  -0.0401   0.0059   1.0000
  17.500   1.3578   0.09297   0.08817  -0.0421   0.0057   1.0000
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