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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 500,000
Max Cl/Cd: 101.96 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe441-il-500000.txt
Download as CSV file: xf-goe441-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 441 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0451   0.10288   0.09998  -0.0936   0.8529   0.0402
 -10.000   0.0537   0.10033   0.09739  -0.0947   0.8423   0.0411
  -9.750   0.0379   0.09439   0.09138  -0.1013   0.8326   0.0431
  -9.500   0.0520   0.09225   0.08921  -0.1009   0.8231   0.0433
  -9.250   0.0667   0.09035   0.08725  -0.1007   0.8140   0.0436
  -9.000   0.0800   0.08842   0.08529  -0.1011   0.8048   0.0439
  -8.750  -0.0653   0.02875   0.02477  -0.1756   0.8000   0.0385
  -8.500  -0.0372   0.02570   0.02144  -0.1810   0.7927   0.0389
  -8.250  -0.0089   0.02410   0.01969  -0.1836   0.7846   0.0394
  -8.000   0.0200   0.02256   0.01793  -0.1860   0.7773   0.0398
  -7.750   0.0499   0.02078   0.01589  -0.1885   0.7699   0.0402
  -7.500   0.0796   0.01939   0.01424  -0.1903   0.7616   0.0406
  -7.250   0.1094   0.01824   0.01287  -0.1917   0.7534   0.0410
  -7.000   0.1391   0.01727   0.01168  -0.1927   0.7443   0.0415
  -6.750   0.1689   0.01646   0.01066  -0.1936   0.7355   0.0421
  -6.500   0.1986   0.01580   0.00981  -0.1943   0.7252   0.0426
  -6.250   0.2281   0.01531   0.00913  -0.1948   0.7144   0.0430
  -6.000   0.2569   0.01442   0.00812  -0.1954   0.7012   0.0439
  -5.750   0.2855   0.01402   0.00767  -0.1956   0.6844   0.0447
  -5.500   0.3137   0.01374   0.00727  -0.1958   0.6622   0.0458
  -5.250   0.3408   0.01353   0.00685  -0.1956   0.6270   0.0468
  -5.000   0.3664   0.01346   0.00648  -0.1952   0.5830   0.0478
  -4.750   0.3929   0.01331   0.00610  -0.1951   0.5589   0.0487
  -4.500   0.4210   0.01309   0.00579  -0.1953   0.5454   0.0501
  -4.250   0.4493   0.01300   0.00560  -0.1954   0.5357   0.0517
  -4.000   0.4781   0.01290   0.00540  -0.1956   0.5278   0.0536
  -3.750   0.5067   0.01276   0.00517  -0.1959   0.5206   0.0559
  -3.500   0.5362   0.01264   0.00504  -0.1962   0.5155   0.0590
  -3.250   0.5657   0.01252   0.00490  -0.1965   0.5105   0.0631
  -3.000   0.5945   0.01250   0.00482  -0.1966   0.5057   0.0684
  -2.750   0.6228   0.01258   0.00485  -0.1967   0.5007   0.0753
  -2.500   0.6520   0.01257   0.00487  -0.1969   0.4974   0.0836
  -2.250   0.6809   0.01259   0.00490  -0.1970   0.4935   0.0915
  -2.000   0.7096   0.01261   0.00491  -0.1971   0.4895   0.0990
  -1.750   0.7376   0.01274   0.00496  -0.1971   0.4856   0.1055
  -1.500   0.7663   0.01279   0.00498  -0.1974   0.4814   0.1123
  -1.250   0.7952   0.01278   0.00497  -0.1975   0.4790   0.1181
  -1.000   0.8245   0.01271   0.00492  -0.1978   0.4759   0.1248
  -0.750   0.8532   0.01272   0.00493  -0.1980   0.4726   0.1312
  -0.500   0.8818   0.01273   0.00493  -0.1981   0.4692   0.1387
  -0.250   0.9100   0.01281   0.00499  -0.1982   0.4659   0.1468
   0.000   0.9384   0.01297   0.00513  -0.1983   0.4622   0.1575
   0.250   0.9671   0.01295   0.00520  -0.1985   0.4601   0.1743
   0.500   0.9957   0.01295   0.00527  -0.1986   0.4573   0.2026
   0.750   1.0242   0.01293   0.00533  -0.1988   0.4543   0.2351
   1.000   1.0527   0.01292   0.00542  -0.1991   0.4513   0.2728
   1.250   1.0811   0.01293   0.00558  -0.1993   0.4485   0.3457
   1.500   1.1089   0.01307   0.00580  -0.1994   0.4453   0.4108
   1.750   1.1366   0.01321   0.00600  -0.1994   0.4425   0.4502
   2.000   1.1640   0.01328   0.00613  -0.1993   0.4400   0.4787
   2.250   1.1912   0.01336   0.00626  -0.1992   0.4373   0.5011
   2.500   1.2183   0.01346   0.00639  -0.1990   0.4344   0.5236
   2.750   1.2450   0.01357   0.00653  -0.1989   0.4316   0.5439
   3.000   1.2715   0.01372   0.00669  -0.1987   0.4287   0.5665
   3.250   1.2985   0.01397   0.00695  -0.1986   0.4252   0.5934
   3.500   1.3248   0.01399   0.00711  -0.1984   0.4229   0.6317
   3.750   1.3508   0.01399   0.00733  -0.1981   0.4202   0.7071
   4.000   1.3722   0.01379   0.00748  -0.1967   0.4175   0.8502
   4.250   1.3949   0.01384   0.00756  -0.1957   0.4148   1.0000
   4.500   1.4204   0.01405   0.00772  -0.1953   0.4120   1.0000
   4.750   1.4459   0.01435   0.00794  -0.1950   0.4089   1.0000
   5.000   1.4713   0.01458   0.00816  -0.1947   0.4062   1.0000
   5.250   1.4960   0.01475   0.00836  -0.1942   0.4038   1.0000
   5.500   1.5206   0.01494   0.00856  -0.1937   0.4011   1.0000
   5.750   1.5447   0.01515   0.00876  -0.1931   0.3984   1.0000
   6.000   1.5682   0.01538   0.00898  -0.1925   0.3957   1.0000
   6.250   1.5913   0.01566   0.00923  -0.1918   0.3928   1.0000
   6.500   1.6151   0.01600   0.00953  -0.1912   0.3897   1.0000
   6.750   1.6354   0.01619   0.00978  -0.1899   0.3873   1.0000
   7.000   1.6562   0.01642   0.01005  -0.1888   0.3845   1.0000
   7.250   1.6771   0.01668   0.01033  -0.1877   0.3816   1.0000
   7.500   1.6976   0.01698   0.01063  -0.1866   0.3788   1.0000
   7.750   1.7179   0.01733   0.01096  -0.1855   0.3759   1.0000
   8.000   1.7395   0.01774   0.01134  -0.1846   0.3729   1.0000
   8.250   1.7584   0.01803   0.01172  -0.1833   0.3702   1.0000
   8.500   1.7768   0.01836   0.01210  -0.1819   0.3666   1.0000
   8.750   1.7942   0.01873   0.01249  -0.1804   0.3627   1.0000
   9.000   1.8106   0.01923   0.01294  -0.1789   0.3583   1.0000
   9.250   1.8279   0.01968   0.01345  -0.1775   0.3544   1.0000
   9.500   1.8453   0.02011   0.01395  -0.1761   0.3503   1.0000
   9.750   1.8612   0.02063   0.01449  -0.1746   0.3460   1.0000
  10.000   1.8754   0.02130   0.01513  -0.1729   0.3414   1.0000
  10.250   1.8919   0.02185   0.01576  -0.1716   0.3374   1.0000
  10.500   1.9079   0.02244   0.01641  -0.1703   0.3327   1.0000
  10.750   1.9210   0.02321   0.01718  -0.1686   0.3278   1.0000
  11.000   1.9339   0.02403   0.01802  -0.1670   0.3226   1.0000
  11.250   1.9483   0.02479   0.01884  -0.1656   0.3169   1.0000
  11.500   1.9590   0.02578   0.01984  -0.1639   0.3114   1.0000
  11.750   1.9708   0.02676   0.02086  -0.1624   0.3061   1.0000
  12.000   1.9829   0.02775   0.02190  -0.1609   0.3001   1.0000
  12.250   1.9897   0.02911   0.02325  -0.1590   0.2942   1.0000
  12.500   2.0008   0.03023   0.02444  -0.1576   0.2879   1.0000
  12.750   2.0059   0.03182   0.02603  -0.1557   0.2805   1.0000
  13.000   2.0133   0.03329   0.02754  -0.1541   0.2737   1.0000
  13.250   2.0168   0.03511   0.02939  -0.1523   0.2662   1.0000
  13.500   2.0201   0.03703   0.03133  -0.1506   0.2585   1.0000
  13.750   2.0186   0.03944   0.03375  -0.1488   0.2499   1.0000
  14.000   2.0191   0.04175   0.03609  -0.1471   0.2410   1.0000
  14.250   2.0127   0.04477   0.03912  -0.1452   0.2324   1.0000
  14.500   2.0064   0.04791   0.04228  -0.1435   0.2222   1.0000
  14.750   1.9950   0.05168   0.04607  -0.1418   0.2109   1.0000
  15.000   1.9784   0.05616   0.05055  -0.1401   0.1992   1.0000
  15.250   1.9576   0.06128   0.05570  -0.1386   0.1870   1.0000
  15.500   1.9318   0.06730   0.06172  -0.1375   0.1738   1.0000
  15.750   1.9020   0.07405   0.06850  -0.1367   0.1600   1.0000
  16.000   1.8690   0.08144   0.07591  -0.1362   0.1464   1.0000
  16.250   1.8350   0.08909   0.08358  -0.1361   0.1341   1.0000
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