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GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 50,000
Max Cl/Cd: 31.16 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe478-il-50000-n5.txt
Download as CSV file: xf-goe478-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2968   0.12549   0.11803  -0.0404   1.0000   0.1388
  -9.750  -0.3092   0.12413   0.11679  -0.0397   1.0000   0.1391
  -9.500  -0.3216   0.12272   0.11550  -0.0384   1.0000   0.1392
  -9.250  -0.3273   0.12057   0.11347  -0.0365   1.0000   0.1395
  -9.000  -0.3283   0.11812   0.11108  -0.0343   1.0000   0.1399
  -8.750  -0.3364   0.11638   0.10943  -0.0322   1.0000   0.1401
  -8.500  -0.3490   0.11490   0.10804  -0.0303   1.0000   0.1400
  -8.000  -0.3576   0.10197   0.09499  -0.0374   0.9928   0.0881
  -7.750  -0.3474   0.09855   0.09158  -0.0397   0.9869   0.0872
  -7.500  -0.3426   0.09494   0.08798  -0.0429   0.9806   0.0866
  -7.250  -0.3414   0.09132   0.08437  -0.0458   0.9731   0.0858
  -7.000  -0.3391   0.08721   0.08023  -0.0496   0.9654   0.0852
  -6.750  -0.3338   0.08255   0.07553  -0.0541   0.9583   0.0843
  -6.500  -0.3343   0.07799   0.07091  -0.0572   0.9503   0.0832
  -6.250  -0.3306   0.07168   0.06441  -0.0627   0.9434   0.0813
  -6.000  -0.3383   0.06413   0.05641  -0.0667   0.9338   0.0794
  -5.750  -0.3202   0.05969   0.05168  -0.0698   0.9276   0.0792
  -5.500  -0.3094   0.05589   0.04757  -0.0705   0.9181   0.0792
  -5.250  -0.2838   0.05266   0.04409  -0.0728   0.9113   0.0802
  -5.000  -0.2656   0.05079   0.04208  -0.0727   0.9024   0.0817
  -4.750  -0.2416   0.04814   0.03913  -0.0740   0.8955   0.0834
  -4.500  -0.2154   0.04527   0.03582  -0.0754   0.8901   0.0848
  -4.250  -0.2009   0.04314   0.03333  -0.0742   0.8817   0.0856
  -4.000  -0.1716   0.04067   0.03035  -0.0752   0.8762   0.0870
  -3.750  -0.1456   0.03884   0.02808  -0.0754   0.8700   0.0892
  -3.500  -0.1242   0.03804   0.02727  -0.0747   0.8619   0.0919
  -3.250  -0.0899   0.03672   0.02567  -0.0759   0.8567   0.0961
  -3.000  -0.0662   0.03554   0.02409  -0.0751   0.8489   0.0992
  -2.750  -0.0382   0.03468   0.02325  -0.0752   0.8416   0.1027
  -2.500   0.0004   0.03366   0.02201  -0.0768   0.8369   0.1100
  -2.250   0.0188   0.03317   0.02152  -0.0752   0.8269   0.1150
  -1.750   0.0857   0.03179   0.02004  -0.0766   0.8136   0.1360
  -1.500   0.1140   0.03135   0.01961  -0.0765   0.8049   0.1510
  -1.250   0.1562   0.03067   0.01897  -0.0785   0.8002   0.1758
  -1.000   0.1737   0.03054   0.01882  -0.0767   0.7886   0.1984
  -0.750   0.2129   0.02987   0.01821  -0.0783   0.7831   0.2366
  -0.500   0.2321   0.02960   0.01813  -0.0769   0.7722   0.2729
  -0.250   0.2670   0.02877   0.01765  -0.0778   0.7657   0.3303
   0.000   0.2876   0.02817   0.01759  -0.0765   0.7558   0.4178
   0.250   0.3810   0.02660   0.01738  -0.0871   0.7519   1.0000
   0.500   0.4180   0.02644   0.01692  -0.0880   0.7454   1.0000
   0.750   0.4310   0.02685   0.01714  -0.0854   0.7326   1.0000
   1.000   0.4674   0.02671   0.01677  -0.0863   0.7263   1.0000
   1.250   0.4789   0.02720   0.01713  -0.0835   0.7133   1.0000
   1.500   0.5149   0.02707   0.01681  -0.0843   0.7071   1.0000
   1.750   0.5247   0.02767   0.01731  -0.0813   0.6939   1.0000
   2.000   0.5602   0.02755   0.01704  -0.0820   0.6879   1.0000
   2.250   0.5681   0.02826   0.01768  -0.0789   0.6747   1.0000
   2.500   0.6036   0.02813   0.01742  -0.0796   0.6690   1.0000
   2.750   0.6097   0.02894   0.01819  -0.0763   0.6560   1.0000
   3.000   0.6455   0.02879   0.01793  -0.0770   0.6507   1.0000
   3.250   0.6502   0.02971   0.01882  -0.0736   0.6381   1.0000
   3.500   0.6867   0.02950   0.01853  -0.0743   0.6331   1.0000
   3.750   0.6902   0.03052   0.01953  -0.0709   0.6209   1.0000
   4.000   0.7192   0.03059   0.01954  -0.0707   0.6144   1.0000
   4.250   0.7304   0.03131   0.02025  -0.0682   0.6042   1.0000
   4.500   0.7606   0.03132   0.02022  -0.0681   0.5979   1.0000
   4.750   0.7723   0.03202   0.02092  -0.0657   0.5879   1.0000
   5.000   0.8070   0.03182   0.02068  -0.0661   0.5819   1.0000
   5.250   0.8180   0.03252   0.02139  -0.0636   0.5714   1.0000
   5.500   0.8513   0.03231   0.02114  -0.0637   0.5642   1.0000
   5.750   0.8683   0.03273   0.02158  -0.0618   0.5540   1.0000
   6.000   0.8957   0.03275   0.02159  -0.0612   0.5452   1.0000
   6.250   0.9219   0.03282   0.02166  -0.0604   0.5357   1.0000
   6.500   0.9415   0.03321   0.02206  -0.0589   0.5257   1.0000
   6.750   0.9765   0.03295   0.02179  -0.0592   0.5162   1.0000
   7.000   0.9861   0.03376   0.02263  -0.0565   0.5050   1.0000
   7.250   1.0325   0.03314   0.02197  -0.0582   0.4954   1.0000
   7.500   1.0282   0.03443   0.02335  -0.0539   0.4831   1.0000
   7.750   1.0526   0.03463   0.02355  -0.0529   0.4721   1.0000
   8.000   1.0709   0.03501   0.02397  -0.0512   0.4601   1.0000
   8.250   1.0737   0.03607   0.02511  -0.0479   0.4478   1.0000
   8.500   1.0966   0.03623   0.02527  -0.0467   0.4360   1.0000
   8.750   1.1049   0.03699   0.02608  -0.0440   0.4232   1.0000
   9.000   1.1055   0.03822   0.02741  -0.0408   0.4102   1.0000
   9.250   1.1160   0.03893   0.02815  -0.0386   0.3973   1.0000
   9.500   1.1326   0.03926   0.02848  -0.0369   0.3843   1.0000
   9.750   1.1321   0.04063   0.02994  -0.0340   0.3703   1.0000
  10.000   1.1322   0.04210   0.03147  -0.0315   0.3561   1.0000
  10.250   1.1357   0.04342   0.03286  -0.0293   0.3420   1.0000
  10.500   1.1405   0.04467   0.03412  -0.0273   0.3275   1.0000
  10.750   1.1458   0.04591   0.03536  -0.0254   0.3130   1.0000
  11.000   1.1510   0.04720   0.03662  -0.0236   0.2983   1.0000
  11.250   1.1566   0.04851   0.03788  -0.0220   0.2839   1.0000
  11.500   1.1619   0.04994   0.03926  -0.0204   0.2701   1.0000
  11.750   1.1617   0.05208   0.04141  -0.0191   0.2568   1.0000
  12.000   1.1632   0.05414   0.04347  -0.0178   0.2444   1.0000
  12.250   1.1683   0.05591   0.04518  -0.0167   0.2333   1.0000
  12.500   1.1732   0.05774   0.04697  -0.0156   0.2228   1.0000
  12.750   1.1724   0.06038   0.04968  -0.0148   0.2129   1.0000
  13.000   1.1804   0.06199   0.05120  -0.0139   0.2040   1.0000
  13.250   1.1777   0.06502   0.05437  -0.0134   0.1952   1.0000
  13.500   1.1850   0.06686   0.05615  -0.0126   0.1876   1.0000
  13.750   1.1819   0.07013   0.05957  -0.0124   0.1801   1.0000
  14.000   1.1922   0.07165   0.06100  -0.0116   0.1733   1.0000
  14.250   1.1839   0.07580   0.06539  -0.0119   0.1672   1.0000
  14.500   1.1926   0.07761   0.06718  -0.0114   0.1611   1.0000
  14.750   1.1892   0.08129   0.07101  -0.0117   0.1562   1.0000
  15.000   1.1803   0.08584   0.07575  -0.0125   0.1513   1.0000
  15.250   1.1924   0.08726   0.07714  -0.0120   0.1466   1.0000
  15.500   1.1820   0.09225   0.08230  -0.0131   0.1429   1.0000
  15.750   1.1521   0.10067   0.09104  -0.0162   0.1395   1.0000
  16.000   1.1307   0.10806   0.09862  -0.0191   0.1361   1.0000
  16.250   1.1484   0.10848   0.09901  -0.0182   0.1329   1.0000
  16.500   1.0028   0.14344   0.13433  -0.0372   0.1276   1.0000
  16.750   0.9775   0.15453   0.14543  -0.0429   0.1232   1.0000
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