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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 100,000
Max Cl/Cd: 51.95 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe441-il-100000-n5.txt
Download as CSV file: xf-goe441-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0522   0.11190   0.10656  -0.0972   0.9081   0.0789
  -9.750   0.0571   0.10934   0.10398  -0.0999   0.8989   0.0792
  -9.500   0.0627   0.10664   0.10127  -0.1023   0.8898   0.0793
  -9.250   0.0690   0.10386   0.09847  -0.1042   0.8804   0.0794
  -9.000   0.0777   0.10086   0.09545  -0.1058   0.8712   0.0794
  -8.750   0.0862   0.09799   0.09257  -0.1070   0.8618   0.0794
  -7.750   0.1250   0.08405   0.07848  -0.1102   0.8269   0.0635
  -7.500   0.1357   0.08157   0.07598  -0.1106   0.8172   0.0623
  -7.250   0.1421   0.07880   0.07319  -0.1115   0.8074   0.0610
  -6.750   0.1354   0.07030   0.06464  -0.1174   0.7875   0.0573
  -6.500   0.1460   0.06717   0.06145  -0.1198   0.7782   0.0571
  -6.250   0.1546   0.06368   0.05795  -0.1231   0.7673   0.0570
  -6.000   0.1660   0.05680   0.05097  -0.1327   0.7584   0.0575
  -5.500   0.2253   0.03744   0.03086  -0.1650   0.7383   0.0589
  -5.250   0.2623   0.03214   0.02496  -0.1740   0.7253   0.0603
  -5.000   0.2999   0.02873   0.02092  -0.1794   0.7131   0.0624
  -4.750   0.3343   0.02677   0.01849  -0.1822   0.7004   0.0650
  -4.500   0.3619   0.02615   0.01777  -0.1827   0.6852   0.0669
  -4.250   0.3923   0.02498   0.01627  -0.1839   0.6697   0.0694
  -4.000   0.4229   0.02387   0.01483  -0.1849   0.6537   0.0720
  -3.750   0.4510   0.02346   0.01431  -0.1851   0.6372   0.0746
  -3.500   0.4811   0.02280   0.01330  -0.1857   0.6217   0.0796
  -3.250   0.5094   0.02254   0.01295  -0.1859   0.6078   0.0834
  -3.000   0.5390   0.02205   0.01218  -0.1863   0.5953   0.0890
  -2.750   0.5676   0.02183   0.01181  -0.1866   0.5846   0.0951
  -2.500   0.5966   0.02155   0.01135  -0.1869   0.5752   0.1024
  -2.250   0.6256   0.02133   0.01095  -0.1872   0.5665   0.1113
  -2.000   0.6544   0.02118   0.01068  -0.1875   0.5590   0.1206
  -1.750   0.6832   0.02106   0.01051  -0.1878   0.5525   0.1300
  -1.500   0.7119   0.02100   0.01039  -0.1881   0.5463   0.1400
  -1.250   0.7409   0.02103   0.01029  -0.1883   0.5408   0.1508
  -1.000   0.7699   0.02109   0.01029  -0.1886   0.5357   0.1615
  -0.750   0.7978   0.02116   0.01035  -0.1887   0.5301   0.1727
  -0.500   0.8262   0.02124   0.01037  -0.1889   0.5250   0.1855
  -0.250   0.8557   0.02132   0.01036  -0.1892   0.5206   0.2001
   0.000   0.8854   0.02141   0.01040  -0.1897   0.5167   0.2182
   0.250   0.9135   0.02146   0.01053  -0.1899   0.5122   0.2402
   0.500   0.9420   0.02154   0.01068  -0.1902   0.5078   0.2722
   0.750   0.9709   0.02165   0.01091  -0.1906   0.5036   0.3198
   1.000   1.0003   0.02186   0.01116  -0.1909   0.4999   0.3829
   1.250   1.0278   0.02213   0.01146  -0.1909   0.4962   0.4374
   1.500   1.0539   0.02239   0.01181  -0.1906   0.4924   0.4815
   1.750   1.0801   0.02266   0.01213  -0.1904   0.4884   0.5222
   2.000   1.1066   0.02290   0.01240  -0.1901   0.4846   0.5616
   2.250   1.1336   0.02314   0.01266  -0.1900   0.4812   0.6027
   2.500   1.1609   0.02339   0.01293  -0.1898   0.4782   0.6499
   2.750   1.1823   0.02359   0.01335  -0.1886   0.4747   0.7101
   3.000   1.2010   0.02362   0.01364  -0.1867   0.4711   0.8102
   3.250   1.2236   0.02383   0.01386  -0.1858   0.4674   1.0000
   3.500   1.2507   0.02425   0.01417  -0.1859   0.4639   1.0000
   3.750   1.2788   0.02467   0.01445  -0.1861   0.4608   1.0000
   4.000   1.3061   0.02514   0.01481  -0.1862   0.4579   1.0000
   4.250   1.3275   0.02566   0.01539  -0.1854   0.4541   1.0000
   4.500   1.3503   0.02616   0.01591  -0.1847   0.4503   1.0000
   4.750   1.3742   0.02663   0.01634  -0.1843   0.4467   1.0000
   5.000   1.3996   0.02706   0.01671  -0.1840   0.4435   1.0000
   5.250   1.4267   0.02748   0.01704  -0.1841   0.4407   1.0000
   5.500   1.4483   0.02805   0.01763  -0.1833   0.4374   1.0000
   5.750   1.4660   0.02868   0.01836  -0.1819   0.4334   1.0000
   6.000   1.4861   0.02925   0.01898  -0.1809   0.4297   1.0000
   6.250   1.5083   0.02974   0.01946  -0.1802   0.4264   1.0000
   6.500   1.5330   0.03015   0.01983  -0.1799   0.4234   1.0000
   6.750   1.5592   0.03058   0.02018  -0.1798   0.4208   1.0000
   7.000   1.5693   0.03146   0.02125  -0.1774   0.4168   1.0000
   7.250   1.5832   0.03221   0.02211  -0.1755   0.4130   1.0000
   7.500   1.6007   0.03282   0.02276  -0.1741   0.4095   1.0000
   7.750   1.6218   0.03330   0.02325  -0.1733   0.4065   1.0000
   8.000   1.6465   0.03371   0.02361  -0.1730   0.4040   1.0000
   8.250   1.6552   0.03465   0.02468  -0.1704   0.4007   1.0000
   8.500   1.6561   0.03581   0.02601  -0.1668   0.3968   1.0000
   8.750   1.6643   0.03676   0.02707  -0.1644   0.3932   1.0000
   9.000   1.6796   0.03743   0.02777  -0.1628   0.3900   1.0000
   9.250   1.7014   0.03784   0.02816  -0.1621   0.3873   1.0000
   9.500   1.7113   0.03883   0.02923  -0.1601   0.3843   1.0000
   9.750   1.6984   0.04099   0.03163  -0.1556   0.3800   1.0000
  10.000   1.6980   0.04265   0.03344  -0.1528   0.3764   1.0000
  10.250   1.7087   0.04372   0.03456  -0.1511   0.3733   1.0000
  10.500   1.7291   0.04420   0.03505  -0.1504   0.3708   1.0000
  10.750   1.7381   0.04543   0.03634  -0.1487   0.3678   1.0000
  11.000   1.6941   0.05047   0.04172  -0.1432   0.3621   1.0000
  11.250   1.6876   0.05307   0.04445  -0.1409   0.3580   1.0000
  11.500   1.7050   0.05373   0.04514  -0.1401   0.3552   1.0000
  11.750   1.7327   0.05357   0.04497  -0.1398   0.3532   1.0000
  12.000   1.5842   0.07116   0.06309  -0.1339   0.3409   1.0000
  12.250   1.6062   0.07128   0.06324  -0.1332   0.3390   1.0000
  12.500   1.6377   0.07029   0.06226  -0.1326   0.3376   1.0000
  13.000   1.5323   0.08996   0.08225  -0.1318   0.3208   1.0000
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