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E591 (e591-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 100,000
Max Cl/Cd: 52.16 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e591-il-100000.txt
Download as CSV file: xf-e591-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1178   0.10555   0.10135  -0.0656   0.9399   0.1240
  -7.000  -0.0733   0.10130   0.09706  -0.0669   0.9373   0.1307
  -6.750  -0.1055   0.10083   0.09667  -0.0738   0.9201   0.1365
  -6.500  -0.0609   0.09520   0.09102  -0.0728   0.9160   0.1397
  -6.250  -0.0347   0.09181   0.08761  -0.0755   0.9095   0.1460
  -6.000  -0.0636   0.08981   0.08569  -0.0820   0.8924   0.1524
  -5.750  -0.0158   0.08547   0.08130  -0.0810   0.8913   0.1561
  -5.500  -0.0238   0.08331   0.07918  -0.0869   0.8753   0.1666
  -5.250  -0.0353   0.04841   0.04323  -0.1325   0.8597   0.0798
  -5.000   0.0282   0.04001   0.03388  -0.1463   0.8571   0.0744
  -4.750   0.0921   0.03544   0.02849  -0.1554   0.8550   0.0765
  -4.500   0.1248   0.03354   0.02595  -0.1574   0.8435   0.0784
  -4.250   0.1749   0.03088   0.02323  -0.1614   0.8400   0.0816
  -4.000   0.2315   0.02863   0.02067  -0.1660   0.8377   0.0888
  -3.750   0.2610   0.02769   0.01975  -0.1663   0.8272   0.0956
  -3.500   0.3121   0.02597   0.01801  -0.1698   0.8225   0.1088
  -3.250   0.3718   0.02410   0.01629  -0.1751   0.8196   0.1352
  -3.000   0.4160   0.02275   0.01544  -0.1784   0.8109   0.2129
  -2.750   0.4636   0.02253   0.01535  -0.1814   0.8031   0.3175
  -2.500   0.5152   0.02232   0.01514  -0.1844   0.7983   0.3643
  -2.250   0.5361   0.02271   0.01558  -0.1825   0.7847   0.3915
  -2.000   0.5858   0.02234   0.01508  -0.1854   0.7787   0.4247
  -1.750   0.6072   0.02252   0.01522  -0.1838   0.7651   0.4442
  -1.500   0.6440   0.02231   0.01493  -0.1847   0.7558   0.4656
  -1.250   0.6745   0.02221   0.01475  -0.1846   0.7444   0.4839
  -1.000   0.7040   0.02213   0.01464  -0.1844   0.7337   0.4993
  -0.750   0.7383   0.02191   0.01430  -0.1851   0.7234   0.5160
  -0.500   0.7653   0.02194   0.01427  -0.1847   0.7117   0.5315
  -0.250   0.8023   0.02173   0.01389  -0.1859   0.7025   0.5496
   0.000   0.8251   0.02189   0.01403  -0.1848   0.6903   0.5652
   0.250   0.8620   0.02171   0.01371  -0.1858   0.6818   0.5831
   0.500   0.8812   0.02193   0.01398  -0.1841   0.6695   0.5982
   0.750   0.9159   0.02185   0.01377  -0.1849   0.6609   0.6177
   1.000   0.9367   0.02206   0.01402  -0.1835   0.6492   0.6355
   1.250   0.9687   0.02207   0.01392  -0.1838   0.6407   0.6569
   1.500   0.9896   0.02228   0.01419  -0.1824   0.6297   0.6776
   1.750   1.0210   0.02232   0.01412  -0.1826   0.6214   0.7030
   2.000   1.0403   0.02256   0.01445  -0.1809   0.6107   0.7275
   2.250   1.0706   0.02254   0.01431  -0.1807   0.6033   0.7572
   2.500   1.0841   0.02283   0.01475  -0.1779   0.5927   0.7875
   2.750   1.1086   0.02273   0.01458  -0.1765   0.5855   0.8281
   3.000   1.1140   0.02285   0.01489  -0.1720   0.5765   0.8810
   3.250   1.1445   0.02273   0.01467  -0.1726   0.5680   1.0000
   3.500   1.1782   0.02331   0.01513  -0.1744   0.5584   1.0000
   3.750   1.2115   0.02367   0.01532  -0.1757   0.5497   1.0000
   4.000   1.2402   0.02419   0.01573  -0.1761   0.5412   1.0000
   4.250   1.2663   0.02464   0.01611  -0.1760   0.5322   1.0000
   4.500   1.2990   0.02504   0.01632  -0.1768   0.5248   1.0000
   4.750   1.3180   0.02567   0.01702  -0.1755   0.5155   1.0000
   5.000   1.3530   0.02594   0.01707  -0.1767   0.5085   1.0000
   5.250   1.3690   0.02672   0.01795  -0.1749   0.4996   1.0000
   5.500   1.3978   0.02709   0.01822  -0.1750   0.4920   1.0000
   5.750   1.4217   0.02772   0.01883  -0.1745   0.4845   1.0000
   6.000   1.4421   0.02833   0.01946  -0.1733   0.4763   1.0000
   6.250   1.4793   0.02861   0.01952  -0.1748   0.4699   1.0000
   6.500   1.4881   0.02957   0.02068  -0.1719   0.4614   1.0000
   6.750   1.5164   0.02995   0.02097  -0.1720   0.4543   1.0000
   7.000   1.5384   0.03068   0.02171  -0.1712   0.4473   1.0000
   7.250   1.5547   0.03143   0.02255  -0.1695   0.4396   1.0000
   7.500   1.5909   0.03169   0.02261  -0.1708   0.4333   1.0000
   7.750   1.5978   0.03281   0.02395  -0.1677   0.4258   1.0000
   8.000   1.6199   0.03337   0.02451  -0.1669   0.4188   1.0000
   8.250   1.6515   0.03386   0.02488  -0.1675   0.4127   1.0000
   8.500   1.6548   0.03504   0.02629  -0.1640   0.4053   1.0000
   8.750   1.6826   0.03545   0.02663  -0.1640   0.3989   1.0000
   9.000   1.7018   0.03634   0.02755  -0.1629   0.3927   1.0000
   9.250   1.7072   0.03747   0.02885  -0.1597   0.3858   1.0000
   9.500   1.7408   0.03771   0.02898  -0.1606   0.3798   1.0000
   9.750   1.7478   0.03899   0.03041  -0.1578   0.3737   1.0000
  10.000   1.7519   0.04017   0.03174  -0.1545   0.3674   1.0000
  10.250   1.7910   0.04026   0.03167  -0.1562   0.3615   1.0000
  10.500   1.7871   0.04188   0.03350  -0.1519   0.3559   1.0000
  10.750   1.7820   0.04331   0.03511  -0.1475   0.3502   1.0000
  11.000   1.8237   0.04330   0.03495  -0.1495   0.3442   1.0000
  11.250   1.8181   0.04501   0.03683  -0.1452   0.3392   1.0000
  11.500   1.7990   0.04721   0.03928  -0.1395   0.3340   1.0000
  11.750   1.8257   0.04754   0.03957  -0.1394   0.3285   1.0000
  12.000   1.8464   0.04850   0.04053  -0.1388   0.3232   1.0000
  12.250   1.8058   0.05211   0.04448  -0.1317   0.3188   1.0000
  12.500   1.8052   0.05392   0.04640  -0.1291   0.3137   1.0000
  12.750   1.8762   0.05222   0.04444  -0.1333   0.3076   1.0000
  13.000   1.8081   0.05798   0.05065  -0.1250   0.3042   1.0000
  13.250   1.7291   0.06657   0.05963  -0.1193   0.2998   1.0000
  13.500   1.7899   0.06361   0.05654  -0.1203   0.2946   1.0000
  13.750   1.8182   0.06396   0.05688  -0.1202   0.2898   1.0000
  14.000   1.1759   0.17210   0.16595  -0.1536   0.2563   1.0000
  14.250   1.1585   0.18052   0.17443  -0.1583   0.2551   1.0000
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