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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 200,000
Max Cl/Cd: 80.54 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe501-il-200000-n5.txt
Download as CSV file: xf-goe501-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 501 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1442   0.09858   0.09459  -0.0897   0.9633   0.0369
 -10.500  -0.1393   0.09270   0.08869  -0.0950   0.9605   0.0383
 -10.250  -0.1389   0.08486   0.08082  -0.1023   0.9581   0.0395
 -10.000  -0.1207   0.08425   0.08022  -0.1027   0.9521   0.0403
  -9.750  -0.1046   0.08132   0.07728  -0.1060   0.9480   0.0412
  -9.250  -0.2644   0.03128   0.02596  -0.1607   0.8987   0.0454
  -9.000  -0.2432   0.03013   0.02478  -0.1612   0.8928   0.0462
  -8.750  -0.2203   0.02903   0.02357  -0.1620   0.8869   0.0470
  -8.500  -0.1942   0.02752   0.02185  -0.1636   0.8829   0.0479
  -8.250  -0.1708   0.02606   0.02016  -0.1646   0.8776   0.0489
  -8.000  -0.1469   0.02472   0.01856  -0.1654   0.8718   0.0503
  -7.750  -0.1193   0.02331   0.01677  -0.1666   0.8677   0.0518
  -7.500  -0.0919   0.02208   0.01526  -0.1675   0.8636   0.0528
  -7.250  -0.0676   0.02127   0.01439  -0.1674   0.8573   0.0537
  -7.000  -0.0392   0.02051   0.01354  -0.1679   0.8525   0.0548
  -6.750  -0.0103   0.01982   0.01272  -0.1684   0.8477   0.0562
  -6.500   0.0153   0.01922   0.01198  -0.1682   0.8411   0.0578
  -6.250   0.0444   0.01857   0.01113  -0.1686   0.8363   0.0595
  -6.000   0.0736   0.01798   0.01035  -0.1690   0.8316   0.0607
  -5.750   0.0990   0.01731   0.00967  -0.1688   0.8252   0.0621
  -5.500   0.1275   0.01679   0.00912  -0.1690   0.8204   0.0637
  -5.250   0.1570   0.01634   0.00858  -0.1694   0.8161   0.0658
  -5.000   0.1829   0.01599   0.00816  -0.1691   0.8093   0.0680
  -4.750   0.2116   0.01563   0.00766  -0.1692   0.8038   0.0698
  -4.500   0.2406   0.01513   0.00712  -0.1694   0.7993   0.0718
  -4.250   0.2668   0.01479   0.00679  -0.1692   0.7935   0.0743
  -4.000   0.2949   0.01450   0.00645  -0.1693   0.7885   0.0773
  -3.750   0.3245   0.01423   0.00608  -0.1696   0.7843   0.0802
  -3.500   0.3515   0.01397   0.00580  -0.1694   0.7789   0.0830
  -3.250   0.3789   0.01371   0.00554  -0.1694   0.7733   0.0873
  -3.000   0.4081   0.01351   0.00526  -0.1695   0.7686   0.0923
  -2.750   0.4360   0.01330   0.00509  -0.1695   0.7633   0.0993
  -2.500   0.4631   0.01313   0.00498  -0.1694   0.7572   0.1117
  -2.250   0.4917   0.01297   0.00487  -0.1695   0.7519   0.1375
  -2.000   0.5198   0.01287   0.00477  -0.1694   0.7463   0.1599
  -1.750   0.5464   0.01279   0.00472  -0.1691   0.7396   0.1770
  -1.500   0.5750   0.01270   0.00462  -0.1691   0.7337   0.1952
  -1.250   0.6019   0.01265   0.00461  -0.1689   0.7272   0.2133
  -1.000   0.6289   0.01259   0.00460  -0.1686   0.7200   0.2338
  -0.750   0.6566   0.01255   0.00456  -0.1684   0.7124   0.2550
  -0.500   0.6825   0.01253   0.00458  -0.1679   0.7025   0.2778
  -0.250   0.7091   0.01252   0.00458  -0.1675   0.6934   0.2992
   0.000   0.7353   0.01252   0.00459  -0.1670   0.6832   0.3196
   0.250   0.7608   0.01253   0.00464  -0.1664   0.6722   0.3404
   0.500   0.7866   0.01255   0.00465  -0.1659   0.6606   0.3595
   0.750   0.8119   0.01257   0.00466  -0.1653   0.6473   0.3776
   1.000   0.8366   0.01260   0.00469  -0.1645   0.6321   0.3947
   1.250   0.8613   0.01264   0.00472  -0.1638   0.6160   0.4112
   1.500   0.8855   0.01271   0.00475  -0.1629   0.5990   0.4274
   1.750   0.9093   0.01281   0.00481  -0.1620   0.5817   0.4457
   2.000   0.9324   0.01294   0.00490  -0.1610   0.5653   0.4672
   2.500   0.9786   0.01325   0.00523  -0.1591   0.5396   0.5330
   2.750   1.0019   0.01339   0.00543  -0.1581   0.5302   0.5814
   3.000   1.0251   0.01350   0.00563  -0.1572   0.5211   0.6358
   3.250   1.0471   0.01348   0.00582  -0.1559   0.5131   0.7348
   3.750   1.0955   0.01369   0.00615  -0.1543   0.4981   1.0000
   4.000   1.1199   0.01393   0.00637  -0.1537   0.4912   1.0000
   4.250   1.1438   0.01422   0.00661  -0.1530   0.4845   1.0000
   4.500   1.1676   0.01450   0.00686  -0.1523   0.4779   1.0000
   4.750   1.1904   0.01478   0.00711  -0.1514   0.4699   1.0000
   5.000   1.2129   0.01509   0.00738  -0.1504   0.4628   1.0000
   5.250   1.2358   0.01535   0.00766  -0.1496   0.4561   1.0000
   5.500   1.2583   0.01565   0.00795  -0.1486   0.4502   1.0000
   5.750   1.2807   0.01595   0.00825  -0.1477   0.4448   1.0000
   6.000   1.3026   0.01622   0.00857  -0.1466   0.4388   1.0000
   6.250   1.3228   0.01653   0.00887  -0.1453   0.4326   1.0000
   6.500   1.3420   0.01684   0.00921  -0.1438   0.4253   1.0000
   6.750   1.3597   0.01718   0.00956  -0.1420   0.4168   1.0000
   7.000   1.3771   0.01753   0.00994  -0.1402   0.4081   1.0000
   7.250   1.3918   0.01796   0.01034  -0.1380   0.3971   1.0000
   7.500   1.4072   0.01837   0.01079  -0.1360   0.3851   1.0000
   7.750   1.4220   0.01884   0.01126  -0.1339   0.3735   1.0000
   8.000   1.4361   0.01936   0.01178  -0.1318   0.3628   1.0000
   8.250   1.4497   0.01992   0.01234  -0.1296   0.3490   1.0000
   8.500   1.4613   0.02057   0.01299  -0.1273   0.3329   1.0000
   8.750   1.4715   0.02134   0.01372  -0.1248   0.3154   1.0000
   9.000   1.4804   0.02221   0.01455  -0.1223   0.2942   1.0000
   9.250   1.4850   0.02336   0.01559  -0.1193   0.2686   1.0000
   9.500   1.4867   0.02477   0.01686  -0.1162   0.2398   1.0000
   9.750   1.4886   0.02629   0.01826  -0.1133   0.2173   1.0000
  10.000   1.4923   0.02779   0.01971  -0.1108   0.2029   1.0000
  10.250   1.4968   0.02930   0.02119  -0.1085   0.1930   1.0000
  10.500   1.5025   0.03079   0.02268  -0.1064   0.1853   1.0000
  10.750   1.5079   0.03235   0.02425  -0.1045   0.1798   1.0000
  11.000   1.5169   0.03370   0.02567  -0.1029   0.1748   1.0000
  11.250   1.5236   0.03526   0.02729  -0.1012   0.1699   1.0000
  11.500   1.5277   0.03707   0.02912  -0.0995   0.1654   1.0000
  11.750   1.5368   0.03853   0.03068  -0.0982   0.1613   1.0000
  12.000   1.5454   0.04006   0.03231  -0.0969   0.1566   1.0000
  12.250   1.5500   0.04198   0.03428  -0.0955   0.1514   1.0000
  12.500   1.5559   0.04385   0.03623  -0.0943   0.1454   1.0000
  12.750   1.5635   0.04561   0.03809  -0.0933   0.1374   1.0000
  13.000   1.5693   0.04759   0.04014  -0.0923   0.1287   1.0000
  13.250   1.5743   0.04972   0.04231  -0.0914   0.1165   1.0000
  13.500   1.5749   0.05236   0.04492  -0.0905   0.1008   1.0000
  13.750   1.5720   0.05548   0.04798  -0.0896   0.0909   1.0000
  14.000   1.5684   0.05879   0.05127  -0.0889   0.0842   1.0000
  14.250   1.5667   0.06198   0.05452  -0.0884   0.0792   1.0000
  14.500   1.5630   0.06552   0.05809  -0.0880   0.0752   1.0000
  14.750   1.5634   0.06863   0.06130  -0.0878   0.0720   1.0000
  15.000   1.5636   0.07184   0.06461  -0.0877   0.0690   1.0000
  15.250   1.5616   0.07542   0.06827  -0.0877   0.0664   1.0000
  15.500   1.5579   0.07934   0.07227  -0.0880   0.0641   1.0000
  15.750   1.5600   0.08248   0.07553  -0.0882   0.0617   1.0000
  16.000   1.5604   0.08590   0.07908  -0.0886   0.0592   1.0000
  16.250   1.5586   0.08970   0.08297  -0.0891   0.0568   1.0000
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