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E591 (e591-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 200,000
Max Cl/Cd: 77.22 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e591-il-200000.txt
Download as CSV file: xf-e591-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.0147   0.09173   0.08837  -0.0863   0.9429   0.0653
  -7.750  -0.0292   0.08469   0.08139  -0.0985   0.9315   0.0701
  -7.500   0.0048   0.08255   0.07923  -0.0968   0.9286   0.0711
  -7.250   0.0325   0.07973   0.07640  -0.0991   0.9251   0.0729
  -7.000   0.0095   0.07227   0.06899  -0.1104   0.9102   0.0787
  -6.750  -0.0233   0.03586   0.03115  -0.1562   0.8918   0.0436
  -6.500   0.0080   0.03200   0.02704  -0.1604   0.8850   0.0426
  -6.250   0.0498   0.02788   0.02230  -0.1666   0.8791   0.0427
  -6.000   0.1025   0.02478   0.01850  -0.1732   0.8761   0.0437
  -5.750   0.1541   0.02223   0.01564  -0.1785   0.8733   0.0445
  -5.500   0.1844   0.02096   0.01432  -0.1791   0.8631   0.0457
  -5.250   0.2304   0.01952   0.01271  -0.1826   0.8573   0.0476
  -5.000   0.2673   0.01840   0.01141  -0.1843   0.8479   0.0500
  -4.750   0.3070   0.01753   0.01052  -0.1866   0.8390   0.0542
  -4.500   0.3408   0.01669   0.00968  -0.1877   0.8279   0.0580
  -4.250   0.3809   0.01587   0.00878  -0.1900   0.8183   0.0636
  -4.000   0.4108   0.01533   0.00825  -0.1904   0.8053   0.0713
  -3.750   0.4478   0.01470   0.00762  -0.1923   0.7944   0.0837
  -3.500   0.4825   0.01397   0.00696  -0.1939   0.7820   0.1137
  -3.250   0.5167   0.01325   0.00667  -0.1958   0.7693   0.2352
  -3.000   0.5499   0.01328   0.00662  -0.1965   0.7579   0.2809
  -2.750   0.5772   0.01337   0.00665  -0.1962   0.7446   0.3074
  -2.500   0.6058   0.01348   0.00667  -0.1960   0.7321   0.3292
  -2.250   0.6366   0.01362   0.00667  -0.1962   0.7207   0.3511
  -2.000   0.6619   0.01376   0.00680  -0.1954   0.7076   0.3718
  -1.750   0.6903   0.01388   0.00683  -0.1952   0.6960   0.3894
  -1.500   0.7182   0.01396   0.00681  -0.1950   0.6842   0.4053
  -1.250   0.7450   0.01408   0.00685  -0.1945   0.6722   0.4211
  -1.000   0.7740   0.01416   0.00684  -0.1945   0.6617   0.4343
  -0.750   0.7993   0.01420   0.00685  -0.1938   0.6496   0.4471
  -0.500   0.8275   0.01431   0.00686  -0.1936   0.6391   0.4605
  -0.250   0.8537   0.01436   0.00689  -0.1931   0.6279   0.4728
   0.000   0.8812   0.01449   0.00692  -0.1929   0.6176   0.4867
   0.250   0.9078   0.01458   0.00698  -0.1924   0.6072   0.5004
   0.500   0.9344   0.01469   0.00707  -0.1920   0.5971   0.5142
   0.750   0.9615   0.01481   0.00713  -0.1917   0.5874   0.5297
   1.000   0.9879   0.01497   0.00725  -0.1913   0.5776   0.5463
   1.250   1.0143   0.01508   0.00735  -0.1908   0.5683   0.5625
   1.500   1.0403   0.01524   0.00752  -0.1903   0.5591   0.5803
   1.750   1.0661   0.01537   0.00764  -0.1898   0.5500   0.5992
   2.000   1.0923   0.01555   0.00782  -0.1894   0.5414   0.6201
   2.250   1.1173   0.01569   0.00799  -0.1887   0.5325   0.6428
   2.500   1.1442   0.01591   0.00816  -0.1884   0.5246   0.6679
   2.750   1.1673   0.01602   0.00839  -0.1873   0.5158   0.6937
   3.000   1.1938   0.01624   0.00855  -0.1869   0.5082   0.7251
   3.250   1.2151   0.01636   0.00882  -0.1855   0.5000   0.7582
   3.500   1.2370   0.01648   0.00899  -0.1841   0.4924   0.7996
   3.750   1.2542   0.01656   0.00914  -0.1816   0.4855   0.8567
   4.000   1.2680   0.01647   0.00915  -0.1786   0.4780   1.0000
   4.250   1.2979   0.01684   0.00933  -0.1792   0.4708   1.0000
   4.500   1.3226   0.01715   0.00964  -0.1787   0.4629   1.0000
   4.750   1.3482   0.01746   0.00987  -0.1784   0.4554   1.0000
   5.000   1.3748   0.01786   0.01017  -0.1783   0.4485   1.0000
   5.250   1.3976   0.01817   0.01050  -0.1774   0.4408   1.0000
   5.500   1.4238   0.01855   0.01075  -0.1772   0.4341   1.0000
   5.750   1.4464   0.01891   0.01114  -0.1763   0.4270   1.0000
   6.000   1.4689   0.01925   0.01145  -0.1754   0.4199   1.0000
   6.250   1.4956   0.01971   0.01179  -0.1754   0.4135   1.0000
   6.500   1.5145   0.02005   0.01222  -0.1738   0.4064   1.0000
   6.750   1.5367   0.02043   0.01255  -0.1729   0.3999   1.0000
   7.000   1.5606   0.02091   0.01297  -0.1723   0.3936   1.0000
   7.250   1.5787   0.02129   0.01342  -0.1707   0.3868   1.0000
   7.500   1.6004   0.02171   0.01378  -0.1697   0.3807   1.0000
   7.750   1.6210   0.02220   0.01428  -0.1686   0.3745   1.0000
   8.000   1.6364   0.02262   0.01476  -0.1665   0.3681   1.0000
   8.250   1.6568   0.02308   0.01515  -0.1654   0.3623   1.0000
   8.500   1.6745   0.02362   0.01572  -0.1638   0.3565   1.0000
   8.750   1.6884   0.02411   0.01629  -0.1615   0.3504   1.0000
   9.000   1.7073   0.02462   0.01674  -0.1602   0.3447   1.0000
   9.250   1.7236   0.02524   0.01739  -0.1585   0.3391   1.0000
   9.500   1.7359   0.02582   0.01807  -0.1562   0.3333   1.0000
   9.750   1.7527   0.02640   0.01861  -0.1546   0.3279   1.0000
  10.000   1.7688   0.02711   0.01934  -0.1530   0.3225   1.0000
  10.250   1.7787   0.02783   0.02017  -0.1505   0.3169   1.0000
  10.500   1.7931   0.02851   0.02085  -0.1487   0.3117   1.0000
  10.750   1.8101   0.02929   0.02161  -0.1474   0.3064   1.0000
  11.000   1.8169   0.03020   0.02266  -0.1447   0.3011   1.0000
  11.250   1.8282   0.03103   0.02354  -0.1427   0.2960   1.0000
  11.500   1.8482   0.03182   0.02424  -0.1419   0.2909   1.0000
  11.750   1.8507   0.03300   0.02560  -0.1389   0.2860   1.0000
  12.000   1.8588   0.03406   0.02673  -0.1368   0.2809   1.0000
  12.250   1.8757   0.03492   0.02752  -0.1358   0.2761   1.0000
  12.500   1.8804   0.03629   0.02903  -0.1334   0.2714   1.0000
  12.750   1.8846   0.03767   0.03054  -0.1312   0.2665   1.0000
  13.000   1.8941   0.03886   0.03174  -0.1296   0.2620   1.0000
  13.250   1.9069   0.04007   0.03296  -0.1284   0.2573   1.0000
  13.500   1.9059   0.04193   0.03500  -0.1261   0.2528   1.0000
  13.750   1.9105   0.04353   0.03667  -0.1244   0.2483   1.0000
  14.000   1.9274   0.04453   0.03758  -0.1237   0.2437   1.0000
  14.250   1.9242   0.04681   0.04007  -0.1217   0.2396   1.0000
  14.500   1.9235   0.04898   0.04238  -0.1200   0.2352   1.0000
  14.750   1.9288   0.05077   0.04420  -0.1188   0.2310   1.0000
  15.000   1.9420   0.05213   0.04553  -0.1181   0.2267   1.0000
  15.250   1.9337   0.05519   0.04882  -0.1166   0.2228   1.0000
  15.500   1.9331   0.05769   0.05144  -0.1155   0.2186   1.0000
  15.750   1.9415   0.05941   0.05314  -0.1148   0.2146   1.0000
  16.000   1.9444   0.06183   0.05564  -0.1141   0.2107   1.0000
  16.250   1.9353   0.06547   0.05948  -0.1134   0.2068   1.0000
  16.500   1.9346   0.06828   0.06238  -0.1129   0.2029   1.0000
  16.750   1.9486   0.06952   0.06354  -0.1124   0.1989   1.0000
  17.000   1.9390   0.07354   0.06777  -0.1122   0.1954   1.0000
  17.250   1.9284   0.07781   0.07223  -0.1123   0.1916   1.0000
  17.500   1.9281   0.08083   0.07532  -0.1123   0.1879   1.0000
  17.750   1.9493   0.08112   0.07547  -0.1117   0.1838   1.0000
  18.000   1.9253   0.08739   0.08205  -0.1126   0.1807   1.0000
  18.250   1.9133   0.09223   0.08706  -0.1135   0.1771   1.0000
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