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EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 59 AIRFOIL (e59-il)
Reynolds number: 1,000,000
Max Cl/Cd: 188.81 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e59-il-1000000.txt
Download as CSV file: xf-e59-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2571   0.08649   0.08480  -0.0609   0.9799   0.0100
  -7.500  -0.2467   0.08334   0.08166  -0.0634   0.9774   0.0105
  -7.250  -0.2316   0.07919   0.07750  -0.0689   0.9748   0.0119
  -7.000  -0.2067   0.07443   0.07274  -0.0766   0.9732   0.0121
  -6.750  -0.1930   0.07054   0.06885  -0.0806   0.9691   0.0121
  -6.500  -0.1749   0.06604   0.06435  -0.0863   0.9650   0.0122
  -6.250  -0.1472   0.05762   0.05591  -0.0996   0.9625   0.0127
  -6.000  -0.1195   0.05534   0.05361  -0.1041   0.9616   0.0134
  -5.750  -0.0842   0.05121   0.04945  -0.1126   0.9607   0.0143
  -5.500  -0.0314   0.04459   0.04273  -0.1267   0.9601   0.0169
  -5.250   0.0760   0.01135   0.00702  -0.1675   0.9607   0.0131
  -5.000   0.1101   0.01090   0.00652  -0.1690   0.9603   0.0142
  -4.750   0.1446   0.01051   0.00607  -0.1705   0.9600   0.0155
  -4.500   0.1789   0.01031   0.00582  -0.1720   0.9597   0.0168
  -4.250   0.2003   0.00963   0.00503  -0.1707   0.9559   0.0188
  -4.000   0.2282   0.00947   0.00487  -0.1707   0.9537   0.0206
  -3.750   0.2595   0.00926   0.00464  -0.1715   0.9525   0.0227
  -3.500   0.2928   0.00879   0.00411  -0.1728   0.9517   0.0258
  -3.250   0.3256   0.00861   0.00394  -0.1738   0.9509   0.0291
  -3.000   0.3591   0.00842   0.00373  -0.1751   0.9502   0.0317
  -2.750   0.3938   0.00814   0.00343  -0.1766   0.9497   0.0338
  -2.500   0.4297   0.00773   0.00300  -0.1784   0.9492   0.0386
  -2.250   0.4663   0.00747   0.00273  -0.1803   0.9485   0.0418
  -2.000   0.5030   0.00719   0.00244  -0.1821   0.9476   0.0442
  -1.750   0.5393   0.00685   0.00211  -0.1839   0.9467   0.0526
  -1.500   0.5627   0.00671   0.00199  -0.1828   0.9421   0.0635
  -1.250   0.5932   0.00644   0.00183  -0.1834   0.9391   0.0961
  -1.000   0.6267   0.00612   0.00171  -0.1847   0.9368   0.1719
  -0.750   0.6636   0.00572   0.00144  -0.1866   0.9322   0.2250
  -0.500   0.6913   0.00534   0.00132  -0.1865   0.9224   0.3420
  -0.250   0.7214   0.00502   0.00126  -0.1870   0.9120   0.4571
   0.000   0.7534   0.00474   0.00119  -0.1878   0.8962   0.5725
   0.250   0.7842   0.00445   0.00118  -0.1884   0.8718   0.7099
   0.500   0.8081   0.00428   0.00122  -0.1872   0.8374   0.8699
   0.750   0.8231   0.00438   0.00120  -0.1838   0.7835   1.0000
   1.000   0.8403   0.00493   0.00136  -0.1814   0.7050   1.0000
   1.250   0.8523   0.00592   0.00169  -0.1779   0.5668   1.0000
   1.500   0.8736   0.00647   0.00192  -0.1766   0.5082   1.0000
   1.750   0.8971   0.00687   0.00210  -0.1758   0.4586   1.0000
   2.000   0.9126   0.00810   0.00253  -0.1736   0.2892   1.0000
   2.250   0.9350   0.00872   0.00281  -0.1726   0.2186   1.0000
   2.500   0.9548   0.00971   0.00325  -0.1713   0.1011   1.0000
   2.750   0.9776   0.01036   0.00361  -0.1703   0.0444   1.0000
   3.000   1.0034   0.01062   0.00384  -0.1699   0.0378   1.0000
   3.250   1.0291   0.01088   0.00411  -0.1694   0.0357   1.0000
   3.500   1.0546   0.01116   0.00440  -0.1689   0.0344   1.0000
   3.750   1.0800   0.01146   0.00473  -0.1684   0.0333   1.0000
   4.000   1.1051   0.01179   0.00508  -0.1678   0.0321   1.0000
   4.250   1.1298   0.01216   0.00548  -0.1671   0.0308   1.0000
   4.500   1.1539   0.01263   0.00600  -0.1663   0.0293   1.0000
   4.750   1.1766   0.01328   0.00674  -0.1653   0.0277   1.0000
   5.000   1.2019   0.01351   0.00698  -0.1648   0.0271   1.0000
   5.250   1.2269   0.01377   0.00725  -0.1643   0.0260   1.0000
   5.500   1.2514   0.01410   0.00760  -0.1637   0.0245   1.0000
   5.750   1.2755   0.01447   0.00800  -0.1630   0.0229   1.0000
   6.000   1.2992   0.01488   0.00841  -0.1623   0.0211   1.0000
   6.250   1.3189   0.01587   0.00948  -0.1608   0.0189   1.0000
   6.500   1.3453   0.01585   0.00945  -0.1606   0.0179   1.0000
   6.750   1.3705   0.01601   0.00961  -0.1602   0.0163   1.0000
   7.000   1.3956   0.01615   0.00974  -0.1597   0.0149   1.0000
   7.250   1.4158   0.01701   0.01063  -0.1583   0.0130   1.0000
   7.500   1.4397   0.01730   0.01095  -0.1577   0.0122   1.0000
   7.750   1.4635   0.01760   0.01125  -0.1570   0.0111   1.0000
   8.000   1.4862   0.01801   0.01165  -0.1562   0.0101   1.0000
   8.250   1.5023   0.01938   0.01316  -0.1540   0.0090   1.0000
   8.500   1.5236   0.01995   0.01381  -0.1529   0.0086   1.0000
   8.750   1.5438   0.02065   0.01459  -0.1516   0.0081   1.0000
   9.000   1.5633   0.02143   0.01545  -0.1501   0.0076   1.0000
   9.250   1.5826   0.02217   0.01627  -0.1487   0.0072   1.0000
   9.500   1.6009   0.02301   0.01719  -0.1471   0.0069   1.0000
   9.750   1.6160   0.02429   0.01857  -0.1450   0.0065   1.0000
  10.000   1.6210   0.02745   0.02208  -0.1413   0.0060   1.0000
  10.250   1.6369   0.02820   0.02295  -0.1393   0.0059   1.0000
  10.500   1.6516   0.02888   0.02373  -0.1372   0.0056   1.0000
  10.750   1.6628   0.03006   0.02504  -0.1345   0.0055   1.0000
  11.000   1.6725   0.03137   0.02650  -0.1317   0.0052   1.0000
  11.250   1.6801   0.03295   0.02824  -0.1286   0.0050   1.0000
  11.500   1.6861   0.03461   0.03008  -0.1255   0.0049   1.0000
  11.750   1.6915   0.03627   0.03190  -0.1224   0.0047   1.0000
  12.000   1.6949   0.03813   0.03392  -0.1192   0.0046   1.0000
  12.250   1.6978   0.03999   0.03592  -0.1162   0.0045   1.0000
  12.500   1.6967   0.04234   0.03846  -0.1129   0.0044   1.0000
  12.750   1.6944   0.04483   0.04112  -0.1097   0.0043   1.0000
  13.000   1.6902   0.04754   0.04401  -0.1068   0.0042   1.0000
  13.250   1.6773   0.05149   0.04819  -0.1036   0.0042   1.0000
  13.500   1.6661   0.05530   0.05219  -0.1012   0.0041   1.0000
  13.750   1.6512   0.05987   0.05698  -0.0993   0.0041   1.0000
  14.000   1.6300   0.06565   0.06300  -0.0982   0.0041   1.0000
  14.250   1.6121   0.07146   0.06901  -0.0983   0.0041   1.0000
  14.500   1.5883   0.07882   0.07659  -0.0999   0.0040   1.0000
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