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EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 682 AIRFOIL (e682-il)
Reynolds number: 500,000
Max Cl/Cd: 87.7 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e682-il-500000-n5.txt
Download as CSV file: xf-e682-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 682 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2945   0.08766   0.08425  -0.0917   0.7875   0.0090
 -11.750  -0.3174   0.07850   0.07514  -0.0960   0.7861   0.0090
 -11.500  -0.3998   0.05447   0.05096  -0.1108   0.7843   0.0086
 -11.250  -0.4212   0.04990   0.04626  -0.1120   0.7825   0.0084
 -11.000  -0.4658   0.04349   0.03955  -0.1102   0.7805   0.0085
 -10.750  -0.4939   0.03937   0.03514  -0.1068   0.7786   0.0086
 -10.500  -0.5079   0.03670   0.03224  -0.1034   0.7770   0.0085
 -10.250  -0.5227   0.03389   0.02913  -0.0991   0.7754   0.0087
 -10.000  -0.5312   0.03173   0.02669  -0.0949   0.7739   0.0087
  -9.750  -0.5325   0.02977   0.02448  -0.0914   0.7726   0.0087
  -9.500  -0.5276   0.02782   0.02226  -0.0887   0.7714   0.0088
  -9.250  -0.5172   0.02625   0.02044  -0.0867   0.7701   0.0090
  -9.000  -0.5037   0.02486   0.01880  -0.0850   0.7687   0.0091
  -8.750  -0.4875   0.02365   0.01738  -0.0836   0.7673   0.0091
  -8.500  -0.4692   0.02276   0.01628  -0.0824   0.7661   0.0093
  -8.250  -0.4495   0.02173   0.01507  -0.0815   0.7650   0.0093
  -8.000  -0.4289   0.02042   0.01360  -0.0807   0.7640   0.0095
  -7.750  -0.4072   0.01925   0.01231  -0.0802   0.7630   0.0097
  -7.500  -0.3850   0.01851   0.01152  -0.0797   0.7621   0.0100
  -7.250  -0.3620   0.01794   0.01089  -0.0792   0.7611   0.0103
  -7.000  -0.3386   0.01732   0.01019  -0.0788   0.7602   0.0106
  -6.750  -0.3151   0.01670   0.00950  -0.0783   0.7593   0.0108
  -6.500  -0.2918   0.01611   0.00883  -0.0778   0.7583   0.0110
  -6.250  -0.2688   0.01555   0.00823  -0.0772   0.7572   0.0112
  -6.000  -0.2457   0.01504   0.00769  -0.0766   0.7562   0.0115
  -5.750  -0.2227   0.01459   0.00720  -0.0760   0.7552   0.0118
  -5.500  -0.1995   0.01418   0.00675  -0.0754   0.7541   0.0121
  -5.250  -0.1759   0.01382   0.00636  -0.0749   0.7530   0.0124
  -5.000  -0.1520   0.01350   0.00600  -0.0744   0.7517   0.0126
  -4.750  -0.1292   0.01306   0.00554  -0.0738   0.7504   0.0131
  -4.500  -0.1052   0.01274   0.00519  -0.0733   0.7493   0.0137
  -4.250  -0.0804   0.01249   0.00492  -0.0730   0.7480   0.0145
  -4.000  -0.0553   0.01227   0.00467  -0.0727   0.7468   0.0155
  -3.750  -0.0298   0.01208   0.00444  -0.0725   0.7456   0.0165
  -3.500  -0.0045   0.01187   0.00419  -0.0722   0.7444   0.0180
  -3.250   0.0210   0.01169   0.00401  -0.0720   0.7431   0.0210
  -3.000   0.0446   0.01138   0.00384  -0.0714   0.7415   0.0459
  -2.750   0.0674   0.01101   0.00369  -0.0709   0.7398   0.0956
  -2.500   0.0894   0.01059   0.00355  -0.0702   0.7380   0.1691
  -2.250   0.1091   0.01000   0.00340  -0.0692   0.7362   0.2860
  -2.000   0.1292   0.00945   0.00324  -0.0683   0.7343   0.3984
  -1.750   0.1464   0.00866   0.00302  -0.0669   0.7325   0.5547
  -1.500   0.1606   0.00831   0.00356  -0.0636   0.7308   0.7766
  -1.250   0.1888   0.00853   0.00372  -0.0636   0.7292   0.8054
  -1.000   0.2164   0.00878   0.00392  -0.0635   0.7274   0.8193
  -0.750   0.2429   0.00903   0.00418  -0.0630   0.7252   0.8295
  -0.500   0.2692   0.00924   0.00440  -0.0625   0.7229   0.8357
  -0.250   0.2958   0.00942   0.00458  -0.0621   0.7205   0.8412
   0.000   0.3239   0.00948   0.00458  -0.0624   0.7182   0.8472
   0.250   0.3507   0.00956   0.00466  -0.0620   0.7160   0.8496
   0.500   0.3784   0.00961   0.00467  -0.0620   0.7140   0.8515
   0.750   0.4062   0.00962   0.00467  -0.0622   0.7117   0.8531
   1.000   0.4331   0.00961   0.00468  -0.0622   0.7086   0.8545
   1.250   0.4607   0.00958   0.00464  -0.0624   0.7052   0.8558
   1.500   0.4889   0.00953   0.00457  -0.0628   0.7019   0.8570
   1.750   0.5177   0.00947   0.00448  -0.0632   0.6988   0.8581
   2.000   0.5452   0.00943   0.00446  -0.0635   0.6946   0.8590
   2.250   0.5728   0.00939   0.00443  -0.0637   0.6898   0.8601
   2.500   0.6011   0.00933   0.00436  -0.0641   0.6854   0.8610
   2.750   0.6290   0.00929   0.00433  -0.0645   0.6801   0.8617
   3.000   0.6564   0.00925   0.00430  -0.0647   0.6735   0.8623
   3.250   0.6831   0.00920   0.00427  -0.0647   0.6670   0.8629
   3.500   0.7092   0.00918   0.00427  -0.0646   0.6582   0.8635
   3.750   0.7354   0.00916   0.00426  -0.0645   0.6483   0.8640
   4.000   0.7609   0.00915   0.00423  -0.0643   0.6360   0.8645
   4.250   0.7852   0.00918   0.00422  -0.0638   0.6195   0.8650
   4.500   0.8075   0.00927   0.00424  -0.0629   0.6000   0.8656
   4.750   0.8279   0.00944   0.00432  -0.0617   0.5782   0.8663
   5.000   0.8469   0.00967   0.00446  -0.0603   0.5559   0.8670
   5.250   0.8648   0.00992   0.00464  -0.0587   0.5345   0.8679
   5.500   0.8819   0.01019   0.00483  -0.0569   0.5136   0.8690
   5.750   0.8973   0.01048   0.00505  -0.0549   0.4936   0.8698
   6.000   0.9093   0.01076   0.00527  -0.0522   0.4731   0.8708
   6.250   0.9207   0.01107   0.00554  -0.0495   0.4540   0.8718
   6.500   0.9308   0.01151   0.00590  -0.0466   0.4328   0.8729
   6.750   0.9408   0.01201   0.00633  -0.0439   0.4098   0.8740
   7.000   0.9481   0.01264   0.00685  -0.0409   0.3838   0.8750
   7.250   0.9553   0.01335   0.00745  -0.0380   0.3566   0.8760
   7.500   0.9619   0.01416   0.00812  -0.0352   0.3275   0.8770
   7.750   0.9655   0.01510   0.00891  -0.0320   0.2950   0.8782
   8.250   0.9774   0.01703   0.01055  -0.0269   0.2306   0.8801
   8.500   0.9862   0.01795   0.01134  -0.0248   0.2047   0.8810
   8.750   0.9951   0.01890   0.01217  -0.0229   0.1784   0.8818
   9.000   1.0066   0.01974   0.01294  -0.0213   0.1585   0.8826
   9.250   1.0183   0.02060   0.01373  -0.0198   0.1405   0.8835
   9.500   1.0282   0.02157   0.01460  -0.0182   0.1200   0.8843
   9.750   1.0376   0.02261   0.01554  -0.0166   0.0986   0.8852
  10.000   1.0473   0.02365   0.01650  -0.0150   0.0802   0.8860
  10.250   1.0555   0.02482   0.01756  -0.0134   0.0610   0.8869
  10.500   1.0641   0.02600   0.01865  -0.0119   0.0444   0.8877
  10.750   1.0719   0.02726   0.01984  -0.0104   0.0302   0.8885
  11.000   1.0806   0.02850   0.02103  -0.0090   0.0190   0.8893
  11.250   1.0905   0.02969   0.02221  -0.0078   0.0134   0.8901
  11.500   1.1012   0.03086   0.02341  -0.0068   0.0109   0.8908
  12.000   1.1234   0.03317   0.02583  -0.0048   0.0091   0.8925
  12.250   1.1346   0.03434   0.02707  -0.0039   0.0086   0.8935
  12.500   1.1448   0.03561   0.02842  -0.0030   0.0083   0.8944
  12.750   1.1550   0.03691   0.02980  -0.0021   0.0080   0.8953
  13.000   1.1630   0.03844   0.03140  -0.0012   0.0075   0.8961
  13.250   1.1712   0.04000   0.03305  -0.0004   0.0073   0.8971
  13.500   1.1770   0.04182   0.03496   0.0004   0.0070   0.8980
  13.750   1.1864   0.04336   0.03658   0.0010   0.0068   0.8989
  14.000   1.1925   0.04524   0.03856   0.0016   0.0067   0.8999
  14.250   1.1985   0.04720   0.04061   0.0022   0.0065   0.9009
  14.500   1.2046   0.04921   0.04272   0.0026   0.0064   0.9019
  14.750   1.2092   0.05144   0.04505   0.0029   0.0063   0.9029
  15.000   1.2126   0.05385   0.04756   0.0031   0.0061   0.9039
  15.250   1.2170   0.05622   0.05003   0.0032   0.0060   0.9049
  15.500   1.2184   0.05903   0.05294   0.0032   0.0060   0.9059
  15.750   1.2209   0.06173   0.05574   0.0031   0.0058   0.9069
  16.000   1.2217   0.06470   0.05881   0.0029   0.0058   0.9080
  16.250   1.2216   0.06786   0.06209   0.0026   0.0057   0.9091
  16.500   1.2211   0.07115   0.06549   0.0021   0.0056   0.9103
  16.750   1.2196   0.07469   0.06914   0.0014   0.0056   0.9115
  17.000   1.2172   0.07844   0.07300   0.0005   0.0055   0.9128
  17.250   1.2148   0.08228   0.07696  -0.0005   0.0055   0.9140
  17.500   1.2118   0.08630   0.08110  -0.0017   0.0054   0.9153
  17.750   1.2067   0.09072   0.08562  -0.0032   0.0052   0.9165
  18.000   1.2021   0.09517   0.09019  -0.0048   0.0052   0.9177
  18.250   1.1985   0.09955   0.09468  -0.0065   0.0052   0.9190
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