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E591 (e591-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 500,000
Max Cl/Cd: 99.47 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e591-il-500000-n5.txt
Download as CSV file: xf-e591-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E591                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3480   0.05459   0.05140  -0.1140   0.9582   0.0126
 -11.000  -0.3700   0.04663   0.04325  -0.1216   0.9472   0.0125
 -10.750  -0.3825   0.04036   0.03680  -0.1280   0.9365   0.0125
 -10.500  -0.3876   0.03445   0.03068  -0.1350   0.9233   0.0126
 -10.250  -0.3687   0.02929   0.02528  -0.1450   0.9130   0.0127
 -10.000  -0.3269   0.02483   0.02048  -0.1577   0.9073   0.0130
  -9.750  -0.2923   0.02265   0.01806  -0.1633   0.8990   0.0131
  -9.500  -0.2488   0.02080   0.01601  -0.1694   0.8925   0.0133
  -9.250  -0.2062   0.01931   0.01438  -0.1747   0.8845   0.0136
  -9.000  -0.1619   0.01824   0.01318  -0.1795   0.8753   0.0139
  -8.750  -0.1239   0.01742   0.01225  -0.1827   0.8638   0.0142
  -8.500  -0.0873   0.01666   0.01135  -0.1854   0.8518   0.0145
  -8.250  -0.0548   0.01602   0.01056  -0.1870   0.8377   0.0149
  -8.000  -0.0250   0.01542   0.00982  -0.1880   0.8240   0.0152
  -7.750   0.0045   0.01490   0.00916  -0.1888   0.8103   0.0156
  -7.500   0.0333   0.01444   0.00855  -0.1894   0.7969   0.0160
  -7.250   0.0613   0.01396   0.00796  -0.1898   0.7830   0.0164
  -7.000   0.0893   0.01358   0.00749  -0.1902   0.7701   0.0169
  -6.750   0.1171   0.01329   0.00710  -0.1903   0.7573   0.0174
  -6.500   0.1447   0.01302   0.00674  -0.1904   0.7440   0.0182
  -6.250   0.1726   0.01277   0.00637  -0.1905   0.7317   0.0191
  -6.000   0.2005   0.01248   0.00599  -0.1906   0.7197   0.0198
  -5.750   0.2285   0.01224   0.00568  -0.1907   0.7069   0.0207
  -5.500   0.2565   0.01204   0.00538  -0.1908   0.6951   0.0217
  -5.250   0.2844   0.01184   0.00508  -0.1908   0.6831   0.0228
  -5.000   0.3129   0.01164   0.00482  -0.1909   0.6714   0.0242
  -4.750   0.3406   0.01151   0.00459  -0.1909   0.6596   0.0258
  -4.500   0.3690   0.01135   0.00437  -0.1909   0.6478   0.0277
  -4.250   0.3971   0.01125   0.00418  -0.1909   0.6368   0.0303
  -4.000   0.4251   0.01113   0.00400  -0.1909   0.6250   0.0333
  -3.750   0.4536   0.01102   0.00384  -0.1910   0.6142   0.0367
  -3.500   0.4814   0.01095   0.00369  -0.1909   0.6033   0.0414
  -3.250   0.5102   0.01083   0.00356  -0.1910   0.5924   0.0498
  -3.000   0.5386   0.01072   0.00345  -0.1912   0.5822   0.0677
  -2.750   0.5679   0.01055   0.00334  -0.1915   0.5715   0.0977
  -2.500   0.5971   0.01038   0.00326  -0.1919   0.5616   0.1429
  -2.250   0.6260   0.01028   0.00322  -0.1922   0.5513   0.1839
  -2.000   0.6542   0.01026   0.00322  -0.1922   0.5420   0.2150
  -1.750   0.6821   0.01028   0.00323  -0.1921   0.5320   0.2377
  -1.500   0.7099   0.01031   0.00327  -0.1920   0.5233   0.2606
  -1.250   0.7378   0.01035   0.00332  -0.1919   0.5140   0.2847
  -1.000   0.7650   0.01043   0.00337  -0.1917   0.5054   0.3027
  -0.750   0.7926   0.01049   0.00342  -0.1915   0.4966   0.3198
  -0.500   0.8194   0.01061   0.00349  -0.1912   0.4884   0.3343
  -0.250   0.8471   0.01067   0.00354  -0.1910   0.4803   0.3441
   0.000   0.8737   0.01079   0.00361  -0.1906   0.4719   0.3538
   0.250   0.9009   0.01089   0.00368  -0.1904   0.4647   0.3631
   0.500   0.9277   0.01100   0.00377  -0.1901   0.4568   0.3732
   0.750   0.9540   0.01114   0.00386  -0.1896   0.4494   0.3820
   1.000   0.9811   0.01123   0.00395  -0.1894   0.4422   0.3933
   1.250   1.0071   0.01138   0.00406  -0.1889   0.4349   0.4031
   1.500   1.0337   0.01150   0.00418  -0.1886   0.4284   0.4144
   1.750   1.0600   0.01163   0.00430  -0.1882   0.4211   0.4258
   2.000   1.0854   0.01180   0.00444  -0.1877   0.4145   0.4379
   2.250   1.1119   0.01191   0.00457  -0.1874   0.4082   0.4504
   2.500   1.1375   0.01207   0.00472  -0.1869   0.4013   0.4640
   2.750   1.1625   0.01225   0.00489  -0.1863   0.3950   0.4776
   3.000   1.1884   0.01238   0.00504  -0.1858   0.3890   0.4925
   3.250   1.2128   0.01255   0.00522  -0.1851   0.3823   0.5082
   3.500   1.2367   0.01274   0.00541  -0.1843   0.3762   0.5241
   3.750   1.2616   0.01288   0.00559  -0.1837   0.3705   0.5419
   4.000   1.2851   0.01307   0.00579  -0.1829   0.3640   0.5604
   4.250   1.3083   0.01327   0.00601  -0.1820   0.3581   0.5795
   4.500   1.3325   0.01345   0.00623  -0.1813   0.3522   0.5999
   4.750   1.3552   0.01367   0.00648  -0.1803   0.3459   0.6234
   5.250   1.4015   0.01409   0.00700  -0.1786   0.3343   0.6734
   5.500   1.4234   0.01434   0.00728  -0.1775   0.3283   0.7041
   5.750   1.4451   0.01456   0.00758  -0.1764   0.3229   0.7404
   6.250   1.4844   0.01496   0.00819  -0.1733   0.3114   0.8463
   6.500   1.4967   0.01506   0.00839  -0.1702   0.3068   1.0000
   6.750   1.5187   0.01536   0.00869  -0.1693   0.3013   1.0000
   7.000   1.5389   0.01574   0.00905  -0.1680   0.2955   1.0000
   7.250   1.5583   0.01614   0.00943  -0.1667   0.2905   1.0000
   7.500   1.5793   0.01648   0.00977  -0.1656   0.2855   1.0000
   7.750   1.5985   0.01690   0.01018  -0.1643   0.2798   1.0000
   8.000   1.6160   0.01740   0.01065  -0.1627   0.2749   1.0000
   8.250   1.6361   0.01778   0.01106  -0.1615   0.2704   1.0000
   8.500   1.6545   0.01825   0.01153  -0.1602   0.2651   1.0000
   8.750   1.6705   0.01883   0.01209  -0.1585   0.2600   1.0000
   9.000   1.6887   0.01931   0.01260  -0.1571   0.2558   1.0000
   9.250   1.7061   0.01984   0.01315  -0.1557   0.2510   1.0000
   9.500   1.7214   0.02049   0.01379  -0.1540   0.2459   1.0000
   9.750   1.7365   0.02116   0.01447  -0.1523   0.2416   1.0000
  10.000   1.7531   0.02176   0.01510  -0.1509   0.2373   1.0000
  10.250   1.7675   0.02250   0.01585  -0.1493   0.2326   1.0000
  10.500   1.7796   0.02339   0.01674  -0.1474   0.2279   1.0000
  10.750   1.7948   0.02411   0.01751  -0.1459   0.2240   1.0000
  11.000   1.8086   0.02494   0.01838  -0.1444   0.2195   1.0000
  11.250   1.8195   0.02597   0.01942  -0.1426   0.2151   1.0000
  11.500   1.8311   0.02700   0.02047  -0.1409   0.2111   1.0000
  11.750   1.8438   0.02797   0.02149  -0.1395   0.2070   1.0000
  12.000   1.8542   0.02914   0.02270  -0.1379   0.2027   1.0000
  12.250   1.8618   0.03054   0.02412  -0.1361   0.1985   1.0000
  12.500   1.8731   0.03172   0.02535  -0.1348   0.1950   1.0000
  12.750   1.8829   0.03305   0.02673  -0.1334   0.1911   1.0000
  13.000   1.8901   0.03463   0.02835  -0.1319   0.1871   1.0000
  13.250   1.8958   0.03640   0.03015  -0.1304   0.1834   1.0000
  13.500   1.9050   0.03791   0.03173  -0.1293   0.1800   1.0000
  13.750   1.9120   0.03967   0.03355  -0.1281   0.1762   1.0000
  14.000   1.9159   0.04177   0.03569  -0.1269   0.1725   1.0000
  14.250   1.9198   0.04394   0.03791  -0.1258   0.1691   1.0000
  14.500   1.9262   0.04592   0.03997  -0.1250   0.1658   1.0000
  14.750   1.9300   0.04823   0.04234  -0.1241   0.1623   1.0000
  15.000   1.9306   0.05096   0.04512  -0.1233   0.1588   1.0000
  15.250   1.9325   0.05360   0.04782  -0.1226   0.1557   1.0000
  15.500   1.9360   0.05614   0.05045  -0.1221   0.1527   1.0000
  15.750   1.9367   0.05907   0.05345  -0.1217   0.1493   1.0000
  16.000   1.9339   0.06252   0.05695  -0.1214   0.1460   1.0000
  16.250   1.9332   0.06576   0.06027  -0.1212   0.1431   1.0000
  16.500   1.9342   0.06884   0.06344  -0.1211   0.1402   1.0000
  16.750   1.9316   0.07247   0.06714  -0.1212   0.1369   1.0000
  17.000   1.9257   0.07663   0.07137  -0.1215   0.1339   1.0000
  17.250   1.9221   0.08053   0.07535  -0.1218   0.1312   1.0000
  17.500   1.9211   0.08409   0.07901  -0.1222   0.1283   1.0000
  17.750   1.9162   0.08829   0.08329  -0.1228   0.1252   1.0000
  18.000   1.9077   0.09309   0.08816  -0.1237   0.1223   1.0000
  18.250   1.9025   0.09743   0.09258  -0.1245   0.1197   1.0000
  18.500   1.9003   0.10133   0.09657  -0.1253   0.1169   1.0000
  18.750   1.8937   0.10594   0.10126  -0.1265   0.1140   1.0000
  19.000   1.8840   0.11108   0.10647  -0.1279   0.1111   1.0000
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