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EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 59 AIRFOIL (e59-il)
Reynolds number: 500,000
Max Cl/Cd: 119.29 at α=0.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e59-il-500000-n5.txt
Download as CSV file: xf-e59-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 59 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1660   0.08996   0.08763  -0.0684   0.9766   0.0085
  -9.250  -0.1617   0.08655   0.08422  -0.0690   0.9746   0.0084
  -9.000  -0.1544   0.08305   0.08072  -0.0694   0.9732   0.0077
  -8.750  -0.1478   0.07934   0.07701  -0.0709   0.9720   0.0074
  -8.500  -0.2355   0.09511   0.09267  -0.0655   0.9793   0.0079
  -8.250  -0.2275   0.09213   0.08968  -0.0670   0.9775   0.0071
  -8.000  -0.2222   0.08911   0.08667  -0.0680   0.9740   0.0066
  -7.750  -0.2135   0.08491   0.08249  -0.0711   0.9715   0.0061
  -7.500  -0.1995   0.08154   0.07912  -0.0746   0.9698   0.0063
  -7.250  -0.1945   0.07870   0.07630  -0.0757   0.9656   0.0064
  -7.000  -0.1856   0.07531   0.07292  -0.0782   0.9609   0.0065
  -6.750  -0.1640   0.07107   0.06868  -0.0842   0.9586   0.0073
  -5.750   0.0260   0.01817   0.01423  -0.1656   0.9457   0.0074
  -5.500   0.0673   0.01501   0.01040  -0.1703   0.9455   0.0081
  -5.250   0.1040   0.01344   0.00845  -0.1729   0.9452   0.0088
  -5.000   0.1382   0.01276   0.00765  -0.1746   0.9446   0.0102
  -4.750   0.1727   0.01207   0.00679  -0.1763   0.9442   0.0113
  -4.500   0.1958   0.01156   0.00614  -0.1754   0.9403   0.0125
  -4.250   0.2258   0.01090   0.00532  -0.1760   0.9381   0.0145
  -4.000   0.2557   0.01067   0.00509  -0.1765   0.9363   0.0184
  -3.750   0.2872   0.01040   0.00474  -0.1773   0.9349   0.0216
  -3.500   0.3197   0.01007   0.00438  -0.1784   0.9338   0.0259
  -3.250   0.3521   0.00988   0.00415  -0.1794   0.9326   0.0300
  -3.000   0.3848   0.00970   0.00391  -0.1804   0.9317   0.0324
  -2.750   0.4186   0.00935   0.00355  -0.1819   0.9309   0.0372
  -2.500   0.4524   0.00913   0.00331  -0.1832   0.9302   0.0407
  -2.250   0.4733   0.00905   0.00319  -0.1816   0.9252   0.0426
  -2.000   0.5021   0.00888   0.00299  -0.1818   0.9221   0.0443
  -1.750   0.5346   0.00863   0.00274  -0.1828   0.9200   0.0492
  -1.500   0.5680   0.00844   0.00256  -0.1840   0.9182   0.0557
  -1.250   0.6045   0.00818   0.00232  -0.1858   0.9160   0.0705
  -1.000   0.6315   0.00790   0.00210  -0.1855   0.9047   0.0936
  -0.750   0.6673   0.00751   0.00185  -0.1871   0.8908   0.1535
  -0.500   0.7037   0.00726   0.00163  -0.1889   0.8757   0.1914
  -0.250   0.7386   0.00704   0.00152  -0.1904   0.8609   0.2483
   0.000   0.7742   0.00676   0.00144  -0.1922   0.8307   0.3857
   0.250   0.8040   0.00674   0.00147  -0.1926   0.7723   0.5374
   0.500   0.8245   0.00704   0.00164  -0.1909   0.7014   0.6362
   0.750   0.8356   0.00769   0.00203  -0.1872   0.5794   0.7751
   1.000   0.8441   0.00791   0.00224  -0.1827   0.5266   0.9270
   1.250   0.8671   0.00822   0.00239  -0.1817   0.4939   1.0000
   1.500   0.8909   0.00859   0.00256  -0.1810   0.4554   1.0000
   1.750   0.9076   0.00964   0.00294  -0.1790   0.3164   1.0000
   2.000   0.9290   0.01036   0.00330  -0.1779   0.2445   1.0000
   2.250   0.9522   0.01090   0.00356  -0.1771   0.1905   1.0000
   2.500   0.9714   0.01195   0.00405  -0.1757   0.0807   1.0000
   2.750   0.9953   0.01243   0.00438  -0.1750   0.0458   1.0000
   3.000   1.0205   0.01273   0.00463  -0.1745   0.0405   1.0000
   3.250   1.0460   0.01298   0.00489  -0.1741   0.0384   1.0000
   3.500   1.0713   0.01324   0.00516  -0.1736   0.0376   1.0000
   3.750   1.0964   0.01351   0.00547  -0.1730   0.0368   1.0000
   4.000   1.1213   0.01381   0.00580  -0.1725   0.0363   1.0000
   4.250   1.1460   0.01412   0.00615  -0.1719   0.0359   1.0000
   4.500   1.1705   0.01445   0.00654  -0.1712   0.0355   1.0000
   4.750   1.1946   0.01482   0.00697  -0.1706   0.0351   1.0000
   5.000   1.2184   0.01521   0.00742  -0.1698   0.0343   1.0000
   5.250   1.2416   0.01567   0.00791  -0.1690   0.0322   1.0000
   5.500   1.2637   0.01626   0.00855  -0.1680   0.0295   1.0000
   5.750   1.2859   0.01682   0.00919  -0.1670   0.0277   1.0000
   6.000   1.3105   0.01702   0.00943  -0.1664   0.0266   1.0000
   6.250   1.3345   0.01728   0.00975  -0.1658   0.0241   1.0000
   6.500   1.3582   0.01756   0.01006  -0.1651   0.0197   1.0000
   6.750   1.3809   0.01798   0.01048  -0.1643   0.0159   1.0000
   7.000   1.4029   0.01848   0.01091  -0.1633   0.0117   1.0000
   7.250   1.4235   0.01913   0.01162  -0.1620   0.0094   1.0000
   7.500   1.4430   0.01990   0.01244  -0.1606   0.0077   1.0000
   7.750   1.4620   0.02074   0.01338  -0.1590   0.0069   1.0000
   8.000   1.4810   0.02155   0.01431  -0.1574   0.0063   1.0000
   8.250   1.4989   0.02242   0.01527  -0.1557   0.0057   1.0000
   8.500   1.5156   0.02335   0.01630  -0.1538   0.0053   1.0000
   8.750   1.5289   0.02469   0.01775  -0.1514   0.0048   1.0000
   9.000   1.5448   0.02558   0.01878  -0.1494   0.0045   1.0000
   9.250   1.5594   0.02662   0.01996  -0.1472   0.0042   1.0000
   9.500   1.5733   0.02772   0.02118  -0.1449   0.0039   1.0000
   9.750   1.5860   0.02893   0.02253  -0.1425   0.0037   1.0000
  10.000   1.5979   0.03019   0.02392  -0.1401   0.0035   1.0000
  10.250   1.6082   0.03163   0.02555  -0.1375   0.0034   1.0000
  10.500   1.6160   0.03333   0.02741  -0.1346   0.0032   1.0000
  10.750   1.6191   0.03563   0.02992  -0.1312   0.0031   1.0000
  11.000   1.6256   0.03750   0.03201  -0.1283   0.0030   1.0000
  11.250   1.6298   0.03962   0.03436  -0.1253   0.0030   1.0000
  11.500   1.6326   0.04189   0.03688  -0.1223   0.0029   1.0000
  11.750   1.6314   0.04464   0.03989  -0.1190   0.0028   1.0000
  12.000   1.6281   0.04761   0.04312  -0.1159   0.0027   1.0000
  12.250   1.6221   0.05096   0.04675  -0.1129   0.0027   1.0000
  12.500   1.6126   0.05477   0.05084  -0.1100   0.0026   1.0000
  12.750   1.6012   0.05892   0.05525  -0.1077   0.0026   1.0000
  13.000   1.5871   0.06365   0.06025  -0.1059   0.0026   1.0000
  13.250   1.5704   0.06900   0.06586  -0.1048   0.0025   1.0000
  13.500   1.5506   0.07524   0.07237  -0.1049   0.0025   1.0000
  13.750   1.5302   0.08211   0.07947  -0.1061   0.0026   1.0000
  14.000   1.5072   0.09033   0.08793  -0.1091   0.0026   1.0000
  14.250   1.4849   0.09949   0.09731  -0.1137   0.0025   1.0000
  14.500   1.4615   0.11006   0.10808  -0.1200   0.0026   1.0000
  14.750   1.4363   0.12242   0.12064  -0.1280   0.0026   1.0000
  15.000   1.4121   0.13616   0.13454  -0.1370   0.0027   1.0000
  15.250   1.3819   0.15258   0.15110  -0.1474   0.0028   1.0000
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