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E591 (e591-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 500,000
Max Cl/Cd: 107.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e591-il-500000.txt
Download as CSV file: xf-e591-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1307   0.05399   0.05145  -0.1207   0.9447   0.0229
  -8.750  -0.1366   0.04578   0.04312  -0.1306   0.9370   0.0219
  -8.500  -0.1341   0.03223   0.02902  -0.1576   0.9220   0.0213
  -8.250  -0.1107   0.02616   0.02235  -0.1677   0.9102   0.0212
  -8.000  -0.0640   0.02196   0.01760  -0.1766   0.9066   0.0212
  -7.750  -0.0312   0.01994   0.01526  -0.1796   0.8964   0.0216
  -7.500   0.0168   0.01815   0.01313  -0.1850   0.8909   0.0221
  -7.250   0.0514   0.01709   0.01183  -0.1871   0.8798   0.0225
  -7.000   0.0903   0.01575   0.01038  -0.1900   0.8706   0.0232
  -6.750   0.1226   0.01508   0.00964  -0.1912   0.8582   0.0237
  -6.500   0.1541   0.01450   0.00895  -0.1922   0.8456   0.0245
  -6.250   0.1865   0.01396   0.00826  -0.1933   0.8335   0.0254
  -6.000   0.2160   0.01346   0.00762  -0.1937   0.8201   0.0264
  -5.750   0.2442   0.01295   0.00709  -0.1940   0.8068   0.0276
  -5.500   0.2735   0.01263   0.00667  -0.1943   0.7940   0.0291
  -5.250   0.3024   0.01222   0.00614  -0.1946   0.7808   0.0304
  -5.000   0.3307   0.01182   0.00571  -0.1948   0.7677   0.0322
  -4.750   0.3593   0.01159   0.00535  -0.1949   0.7549   0.0342
  -4.500   0.3885   0.01121   0.00492  -0.1953   0.7420   0.0370
  -4.250   0.4171   0.01093   0.00458  -0.1955   0.7292   0.0407
  -4.000   0.4458   0.01072   0.00429  -0.1956   0.7169   0.0457
  -3.750   0.4744   0.01052   0.00404  -0.1957   0.7042   0.0523
  -3.500   0.5034   0.01029   0.00379  -0.1959   0.6920   0.0644
  -3.250   0.5335   0.00992   0.00353  -0.1966   0.6800   0.1123
  -3.000   0.5633   0.00957   0.00341  -0.1973   0.6677   0.1900
  -2.750   0.5915   0.00951   0.00339  -0.1973   0.6561   0.2329
  -2.500   0.6189   0.00953   0.00339  -0.1971   0.6441   0.2600
  -2.250   0.6465   0.00955   0.00339  -0.1968   0.6328   0.2809
  -2.000   0.6735   0.00965   0.00341  -0.1965   0.6215   0.2981
  -1.750   0.7008   0.00969   0.00343  -0.1962   0.6101   0.3136
  -1.500   0.7280   0.00978   0.00348  -0.1959   0.5996   0.3300
  -1.250   0.7550   0.00986   0.00352  -0.1956   0.5886   0.3461
  -1.000   0.7820   0.00996   0.00357  -0.1952   0.5784   0.3602
  -0.750   0.8087   0.01007   0.00363  -0.1948   0.5680   0.3749
  -0.500   0.8359   0.01014   0.00369  -0.1945   0.5583   0.3872
  -0.250   0.8624   0.01027   0.00374  -0.1941   0.5482   0.3984
   0.000   0.8896   0.01034   0.00380  -0.1938   0.5390   0.4092
   0.250   0.9160   0.01048   0.00387  -0.1934   0.5296   0.4206
   0.500   0.9430   0.01056   0.00396  -0.1931   0.5208   0.4323
   0.750   0.9693   0.01070   0.00403  -0.1927   0.5116   0.4442
   1.000   0.9960   0.01080   0.00414  -0.1924   0.5035   0.4576
   1.250   1.0226   0.01092   0.00424  -0.1920   0.4949   0.4707
   1.750   1.0752   0.01117   0.00449  -0.1912   0.4788   0.5009
   2.000   1.1006   0.01135   0.00463  -0.1907   0.4709   0.5167
   2.250   1.1273   0.01145   0.00477  -0.1903   0.4636   0.5344
   2.500   1.1529   0.01160   0.00492  -0.1898   0.4558   0.5533
   2.750   1.1784   0.01177   0.00509  -0.1893   0.4489   0.5731
   3.000   1.2044   0.01189   0.00525  -0.1889   0.4416   0.5952
   3.250   1.2288   0.01209   0.00545  -0.1882   0.4343   0.6188
   3.500   1.2545   0.01222   0.00564  -0.1877   0.4278   0.6440
   3.750   1.2794   0.01237   0.00583  -0.1871   0.4208   0.6718
   4.000   1.3025   0.01260   0.00607  -0.1862   0.4139   0.7029
   4.250   1.3271   0.01268   0.00627  -0.1855   0.4076   0.7377
   4.500   1.3491   0.01283   0.00648  -0.1843   0.4010   0.7791
   4.750   1.3680   0.01298   0.00672  -0.1824   0.3948   0.8361
   5.000   1.3798   0.01286   0.00679  -0.1789   0.3893   1.0000
   5.250   1.4027   0.01313   0.00701  -0.1780   0.3828   1.0000
   5.500   1.4247   0.01345   0.00726  -0.1770   0.3766   1.0000
   5.750   1.4485   0.01367   0.00748  -0.1762   0.3705   1.0000
   6.000   1.4701   0.01397   0.00774  -0.1752   0.3640   1.0000
   6.250   1.4915   0.01430   0.00804  -0.1740   0.3582   1.0000
   6.500   1.5140   0.01456   0.00830  -0.1731   0.3521   1.0000
   6.750   1.5341   0.01492   0.00861  -0.1718   0.3459   1.0000
   7.000   1.5547   0.01527   0.00895  -0.1706   0.3402   1.0000
   7.250   1.5763   0.01556   0.00926  -0.1696   0.3344   1.0000
   7.500   1.5952   0.01598   0.00963  -0.1681   0.3284   1.0000
   7.750   1.6145   0.01638   0.01003  -0.1667   0.3229   1.0000
   8.000   1.6350   0.01673   0.01040  -0.1656   0.3174   1.0000
   8.250   1.6527   0.01720   0.01084  -0.1640   0.3117   1.0000
   8.500   1.6704   0.01768   0.01132  -0.1625   0.3064   1.0000
   8.750   1.6898   0.01808   0.01175  -0.1612   0.3010   1.0000
   9.000   1.7064   0.01862   0.01228  -0.1596   0.2956   1.0000
   9.250   1.7219   0.01923   0.01288  -0.1578   0.2904   1.0000
   9.500   1.7405   0.01968   0.01338  -0.1565   0.2853   1.0000
   9.750   1.7560   0.02029   0.01399  -0.1548   0.2801   1.0000
  10.000   1.7685   0.02110   0.01476  -0.1528   0.2749   1.0000
  10.250   1.7864   0.02160   0.01535  -0.1515   0.2704   1.0000
  10.500   1.8013   0.02229   0.01606  -0.1499   0.2653   1.0000
  10.750   1.8124   0.02321   0.01696  -0.1479   0.2603   1.0000
  11.000   1.8273   0.02394   0.01774  -0.1464   0.2559   1.0000
  11.250   1.8414   0.02473   0.01858  -0.1448   0.2511   1.0000
  11.500   1.8519   0.02576   0.01960  -0.1430   0.2463   1.0000
  11.750   1.8624   0.02684   0.02070  -0.1412   0.2418   1.0000
  12.000   1.8761   0.02772   0.02166  -0.1398   0.2374   1.0000
  12.250   1.8863   0.02887   0.02283  -0.1381   0.2327   1.0000
  12.500   1.8923   0.03036   0.02432  -0.1361   0.2282   1.0000
  12.750   1.9048   0.03142   0.02547  -0.1349   0.2243   1.0000
  13.000   1.9148   0.03270   0.02680  -0.1335   0.2199   1.0000
  13.250   1.9207   0.03434   0.02845  -0.1318   0.2156   1.0000
  13.500   1.9265   0.03606   0.03021  -0.1303   0.2116   1.0000
  13.750   1.9369   0.03743   0.03168  -0.1292   0.2076   1.0000
  14.000   1.9431   0.03922   0.03350  -0.1279   0.2034   1.0000
  14.250   1.9448   0.04148   0.03577  -0.1265   0.1993   1.0000
  14.500   1.9516   0.04332   0.03770  -0.1255   0.1957   1.0000
  14.750   1.9584   0.04522   0.03968  -0.1246   0.1918   1.0000
  15.000   1.9608   0.04761   0.04211  -0.1236   0.1879   1.0000
  15.250   1.9586   0.05055   0.04506  -0.1226   0.1840   1.0000
  15.500   1.9657   0.05259   0.04722  -0.1221   0.1808   1.0000
  15.750   1.9691   0.05508   0.04979  -0.1215   0.1770   1.0000
  16.000   1.9680   0.05813   0.05288  -0.1210   0.1734   1.0000
  16.250   1.9646   0.06154   0.05632  -0.1205   0.1698   1.0000
  16.500   1.9688   0.06412   0.05903  -0.1203   0.1666   1.0000
  16.750   1.9690   0.06724   0.06222  -0.1201   0.1630   1.0000
  17.000   1.9648   0.07097   0.06599  -0.1201   0.1596   1.0000
  17.250   1.9604   0.07480   0.06987  -0.1202   0.1562   1.0000
  17.500   1.9616   0.07798   0.07318  -0.1204   0.1531   1.0000
  17.750   1.9591   0.08168   0.07696  -0.1208   0.1498   1.0000
  18.000   1.9523   0.08603   0.08134  -0.1213   0.1465   1.0000
  18.250   1.9473   0.09018   0.08556  -0.1219   0.1433   1.0000
  18.500   1.9463   0.09384   0.08935  -0.1226   0.1403   1.0000
  18.750   1.9417   0.09802   0.09359  -0.1234   0.1370   1.0000
  19.000   1.9331   0.10281   0.09841  -0.1245   0.1339   1.0000
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