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E591 (e591-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 50,000
Max Cl/Cd: 34.39 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e591-il-50000-n5.txt
Download as CSV file: xf-e591-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2174   0.15029   0.14346  -0.0355   1.0000   0.1088
 -10.750  -0.2294   0.14974   0.14302  -0.0353   1.0000   0.1097
 -10.500  -0.2413   0.14909   0.14249  -0.0348   1.0000   0.1101
 -10.250  -0.2270   0.14471   0.13818  -0.0326   1.0000   0.1116
 -10.000  -0.2252   0.14261   0.13615  -0.0308   1.0000   0.1132
  -9.750  -0.2279   0.14096   0.13460  -0.0293   1.0000   0.1143
  -9.500  -0.2248   0.13867   0.13236  -0.0297   0.9984   0.1157
  -9.250  -0.2075   0.13487   0.12856  -0.0342   0.9928   0.1173
  -9.000  -0.1920   0.13102   0.12471  -0.0383   0.9866   0.1177
  -8.500  -0.1756   0.11820   0.11177  -0.0499   0.9735   0.0675
  -8.250  -0.1761   0.11244   0.10604  -0.0556   0.9644   0.0625
  -8.000  -0.1612   0.10884   0.10243  -0.0582   0.9563   0.0617
  -7.750  -0.1474   0.10480   0.09840  -0.0621   0.9490   0.0613
  -7.500  -0.1404   0.10096   0.09459  -0.0651   0.9390   0.0612
  -7.250  -0.1355   0.09718   0.09083  -0.0679   0.9285   0.0612
  -7.000  -0.1308   0.09298   0.08666  -0.0713   0.9192   0.0613
  -6.750  -0.1278   0.08916   0.08287  -0.0740   0.9086   0.0610
  -6.500  -0.1302   0.08543   0.07918  -0.0759   0.8960   0.0608
  -6.250  -0.1266   0.08031   0.07407  -0.0804   0.8854   0.0604
  -6.000  -0.1227   0.07351   0.06724  -0.0875   0.8747   0.0596
  -5.750  -0.1250   0.06269   0.05620  -0.1016   0.8610   0.0583
  -5.500  -0.0905   0.05176   0.04450  -0.1199   0.8549   0.0584
  -5.250  -0.0642   0.04724   0.03944  -0.1260   0.8438   0.0599
  -5.000  -0.0170   0.04295   0.03448  -0.1337   0.8386   0.0636
  -4.750   0.0144   0.04107   0.03238  -0.1360   0.8297   0.0666
  -4.500   0.0552   0.03851   0.02927  -0.1397   0.8227   0.0701
  -4.250   0.0984   0.03676   0.02741  -0.1428   0.8181   0.0759
  -4.000   0.1242   0.03572   0.02621  -0.1432   0.8071   0.0808
  -3.750   0.1659   0.03422   0.02454  -0.1457   0.8013   0.0890
  -3.500   0.2012   0.03312   0.02334  -0.1472   0.7933   0.0991
  -3.250   0.2363   0.03210   0.02234  -0.1489   0.7847   0.1129
  -3.000   0.2858   0.03060   0.02096  -0.1530   0.7800   0.1437
  -2.750   0.3171   0.03001   0.02064  -0.1545   0.7688   0.1935
  -2.500   0.3630   0.02958   0.02033  -0.1575   0.7624   0.2751
  -2.250   0.3919   0.02988   0.02068  -0.1575   0.7522   0.3233
  -2.000   0.4280   0.02991   0.02064  -0.1582   0.7441   0.3641
  -1.750   0.4601   0.02996   0.02060  -0.1584   0.7354   0.3951
  -1.500   0.4918   0.02992   0.02041  -0.1587   0.7257   0.4209
  -1.250   0.5313   0.02957   0.01989  -0.1601   0.7188   0.4436
  -1.000   0.5538   0.02973   0.02000  -0.1590   0.7073   0.4591
  -0.750   0.5967   0.02925   0.01933  -0.1608   0.7012   0.4793
  -0.500   0.6162   0.02956   0.01958  -0.1595   0.6887   0.4934
  -0.250   0.6576   0.02914   0.01898  -0.1611   0.6821   0.5129
   0.000   0.6782   0.02949   0.01926  -0.1601   0.6701   0.5287
   0.250   0.7175   0.02915   0.01877  -0.1614   0.6630   0.5485
   0.500   0.7371   0.02953   0.01912  -0.1601   0.6515   0.5646
   0.750   0.7736   0.02930   0.01877  -0.1610   0.6441   0.5853
   1.000   0.7931   0.02967   0.01916  -0.1596   0.6332   0.6026
   1.250   0.8270   0.02953   0.01892  -0.1602   0.6253   0.6256
   1.500   0.8476   0.02991   0.01930  -0.1590   0.6153   0.6464
   1.750   0.8762   0.02988   0.01925  -0.1586   0.6070   0.6708
   2.000   0.8976   0.03014   0.01953  -0.1573   0.5979   0.6963
   2.250   0.9212   0.03030   0.01970  -0.1563   0.5892   0.7264
   2.500   0.9458   0.03027   0.01968  -0.1552   0.5818   0.7619
   2.750   0.9565   0.03066   0.02018  -0.1522   0.5722   0.8024
   3.000   0.9773   0.03023   0.01977  -0.1499   0.5660   0.8805
   3.250   0.9935   0.03097   0.02050  -0.1488   0.5557   1.0000
   3.500   1.0323   0.03118   0.02047  -0.1508   0.5482   1.0000
   3.750   1.0541   0.03201   0.02122  -0.1505   0.5390   1.0000
   4.000   1.0834   0.03249   0.02156  -0.1510   0.5310   1.0000
   4.250   1.1126   0.03297   0.02190  -0.1513   0.5235   1.0000
   4.500   1.1300   0.03388   0.02280  -0.1502   0.5144   1.0000
   4.750   1.1679   0.03396   0.02269  -0.1516   0.5083   1.0000
   5.000   1.1751   0.03532   0.02411  -0.1491   0.4989   1.0000
   5.250   1.2043   0.03570   0.02439  -0.1493   0.4918   1.0000
   5.500   1.2235   0.03655   0.02523  -0.1484   0.4843   1.0000
   5.750   1.2372   0.03759   0.02628  -0.1467   0.4763   1.0000
   6.000   1.2756   0.03762   0.02616  -0.1480   0.4705   1.0000
   6.250   1.2709   0.03943   0.02810  -0.1441   0.4617   1.0000
   6.500   1.2952   0.04001   0.02865  -0.1437   0.4550   1.0000
   6.750   1.3191   0.04065   0.02925  -0.1432   0.4488   1.0000
   7.000   1.3143   0.04264   0.03136  -0.1396   0.4404   1.0000
   7.250   1.3471   0.04276   0.03140  -0.1401   0.4346   1.0000
   7.500   1.3443   0.04480   0.03357  -0.1369   0.4273   1.0000
   7.750   1.3487   0.04651   0.03535  -0.1347   0.4201   1.0000
   8.000   1.3895   0.04610   0.03483  -0.1357   0.4151   1.0000
   8.250   1.3548   0.05037   0.03935  -0.1304   0.4063   1.0000
   8.500   1.3703   0.05151   0.04050  -0.1294   0.4002   1.0000
   8.750   1.4192   0.05036   0.03926  -0.1307   0.3961   1.0000
   9.000   1.3408   0.05892   0.04819  -0.1245   0.3848   1.0000
   9.250   1.3771   0.05822   0.04745  -0.1244   0.3805   1.0000
   9.500   1.2936   0.06990   0.05943  -0.1218   0.3670   1.0000
   9.750   1.3236   0.06947   0.05900  -0.1211   0.3632   1.0000
  10.000   1.3730   0.06694   0.05641  -0.1207   0.3609   1.0000
  10.500   1.3190   0.07990   0.06964  -0.1198   0.3431   1.0000
  11.000   1.2741   0.09373   0.08369  -0.1213   0.3249   1.0000
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