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GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 437 AIRFOIL (goe437-il)
Reynolds number: 100,000
Max Cl/Cd: 59.83 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe437-il-100000.txt
Download as CSV file: xf-goe437-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 437 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3353   0.10607   0.10132  -0.0297   1.0000   0.0573
  -8.000  -0.3445   0.10527   0.10065  -0.0303   1.0000   0.0575
  -7.750  -0.3477   0.10374   0.09921  -0.0323   1.0000   0.0577
  -7.500  -0.3241   0.09506   0.09050  -0.0271   1.0000   0.0602
  -7.250  -0.3213   0.09242   0.08790  -0.0257   1.0000   0.0626
  -7.000  -0.3250   0.09045   0.08602  -0.0245   1.0000   0.0645
  -6.750  -0.3278   0.08843   0.08409  -0.0245   1.0000   0.0672
  -6.500  -0.3306   0.08673   0.08248  -0.0260   1.0000   0.0691
  -6.250  -0.3309   0.08604   0.08183  -0.0330   1.0000   0.0705
  -6.000  -0.3283   0.08294   0.07878  -0.0348   1.0000   0.0711
  -5.750  -0.3308   0.07883   0.07477  -0.0271   1.0000   0.0730
  -5.500  -0.3299   0.07640   0.07239  -0.0252   1.0000   0.0751
  -5.250  -0.3280   0.07409   0.07012  -0.0250   1.0000   0.0780
  -4.750  -0.3024   0.06874   0.06463  -0.0354   1.0000   0.0844
  -4.500  -0.3035   0.06564   0.06162  -0.0313   1.0000   0.0860
  -4.250  -0.2973   0.06315   0.05915  -0.0301   1.0000   0.0890
  -4.000  -0.2613   0.06028   0.05592  -0.0398   1.0000   0.0976
  -3.750  -0.2544   0.05651   0.05227  -0.0376   0.9987   0.0997
  -3.500  -0.1994   0.05220   0.04760  -0.0478   0.9920   0.1119
  -3.000  -0.1182   0.04458   0.03969  -0.0581   0.9779   0.1406
  -2.750  -0.0756   0.04102   0.03598  -0.0629   0.9711   0.1564
  -2.500  -0.0312   0.03843   0.03303  -0.0676   0.9624   0.1794
  -2.250   0.0357   0.02955   0.02274  -0.0735   0.9593   0.0800
  -2.000   0.0821   0.02662   0.01905  -0.0765   0.9525   0.0823
  -1.750   0.1265   0.02393   0.01569  -0.0790   0.9447   0.0845
  -1.500   0.1681   0.02256   0.01413  -0.0815   0.9348   0.0999
  -1.250   0.2180   0.02121   0.01251  -0.0851   0.9270   0.1235
  -1.000   0.2606   0.01994   0.01119  -0.0875   0.9162   0.1499
  -0.750   0.3021   0.01875   0.01011  -0.0896   0.9052   0.1879
  -0.500   0.3459   0.01756   0.00912  -0.0922   0.8958   0.2515
  -0.250   0.4057   0.01474   0.00826  -0.0979   0.8899   1.0000
   0.000   0.4455   0.01452   0.00762  -0.0993   0.8770   1.0000
   0.250   0.4829   0.01430   0.00716  -0.1004   0.8635   1.0000
   0.500   0.5185   0.01409   0.00676  -0.1011   0.8489   1.0000
   0.750   0.5521   0.01392   0.00642  -0.1014   0.8336   1.0000
   1.000   0.5842   0.01379   0.00614  -0.1014   0.8178   1.0000
   1.250   0.6110   0.01384   0.00607  -0.1006   0.7983   1.0000
   1.500   0.6391   0.01389   0.00599  -0.1000   0.7802   1.0000
   1.750   0.6671   0.01397   0.00594  -0.0994   0.7628   1.0000
   2.000   0.6923   0.01417   0.00603  -0.0985   0.7434   1.0000
   2.250   0.7179   0.01438   0.00614  -0.0976   0.7251   1.0000
   2.500   0.7439   0.01459   0.00625  -0.0968   0.7077   1.0000
   2.750   0.7690   0.01484   0.00645  -0.0959   0.6902   1.0000
   3.000   0.7934   0.01510   0.00668  -0.0950   0.6721   1.0000
   3.250   0.8183   0.01536   0.00689  -0.0942   0.6551   1.0000
   3.500   0.8435   0.01560   0.00709  -0.0934   0.6388   1.0000
   3.750   0.8689   0.01587   0.00736  -0.0926   0.6232   1.0000
   4.000   0.8940   0.01618   0.00765  -0.0919   0.6077   1.0000
   4.250   0.9187   0.01654   0.00802  -0.0912   0.5923   1.0000
   4.500   0.9437   0.01693   0.00843  -0.0905   0.5777   1.0000
   4.750   0.9688   0.01738   0.00890  -0.0899   0.5640   1.0000
   5.000   0.9940   0.01786   0.00946  -0.0892   0.5507   1.0000
   5.250   1.0192   0.01838   0.01003  -0.0886   0.5379   1.0000
   5.500   1.0439   0.01889   0.01062  -0.0879   0.5244   1.0000
   5.750   1.0649   0.01910   0.01088  -0.0863   0.5014   1.0000
   6.000   1.0838   0.01895   0.01067  -0.0839   0.4698   1.0000
   6.250   1.1026   0.01896   0.01079  -0.0819   0.4432   1.0000
   6.500   1.1191   0.01886   0.01080  -0.0794   0.4097   1.0000
   6.750   1.1308   0.01890   0.01076  -0.0760   0.3492   1.0000
   7.000   1.1361   0.02017   0.01129  -0.0722   0.2091   1.0000
   7.250   1.1324   0.02347   0.01337  -0.0682   0.0703   1.0000
   7.500   1.1435   0.02516   0.01506  -0.0656   0.0573   1.0000
   7.750   1.1536   0.02675   0.01677  -0.0629   0.0507   1.0000
   8.000   1.1624   0.02828   0.01851  -0.0601   0.0470   1.0000
   8.250   1.1668   0.03003   0.02038  -0.0569   0.0450   1.0000
   8.500   1.1696   0.03196   0.02236  -0.0534   0.0438   1.0000
   8.750   1.1811   0.03411   0.02448  -0.0510   0.0430   1.0000
   9.000   1.2088   0.03644   0.02685  -0.0505   0.0424   1.0000
   9.250   1.2355   0.03874   0.02933  -0.0499   0.0408   1.0000
   9.500   1.2619   0.04140   0.03222  -0.0494   0.0393   1.0000
   9.750   1.2896   0.04496   0.03608  -0.0490   0.0400   1.0000
  10.000   1.3106   0.04900   0.04053  -0.0480   0.0413   1.0000
  10.250   1.3353   0.05582   0.04760  -0.0483   0.0433   1.0000
  10.500   1.3379   0.05591   0.04832  -0.0438   0.0458   1.0000
  10.750   1.3279   0.06009   0.05320  -0.0397   0.0493   1.0000
  11.000   1.3502   0.06690   0.06019  -0.0397   0.0552   1.0000
  11.250   1.3178   0.06860   0.06250  -0.0338   0.0570   1.0000
  11.500   1.2890   0.07196   0.06623  -0.0299   0.0585   1.0000
  11.750   1.2642   0.07626   0.07081  -0.0280   0.0601   1.0000
  12.000   1.2422   0.08118   0.07596  -0.0276   0.0616   1.0000
  12.500   1.2070   0.09240   0.08757  -0.0294   0.0676   1.0000
  12.750   1.1819   0.09845   0.09377  -0.0321   0.0675   1.0000
  13.000   1.1569   0.10533   0.10077  -0.0360   0.0673   1.0000
  13.250   1.1336   0.11283   0.10835  -0.0406   0.0670   1.0000
  13.500   1.1089   0.12140   0.11694  -0.0464   0.0668   1.0000
  13.750   1.0821   0.13149   0.12706  -0.0536   0.0667   1.0000
  14.000   1.0349   0.14861   0.14410  -0.0676   0.0634   1.0000
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