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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 200,000
Max Cl/Cd: 84.02 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe447-il-200000.txt
Download as CSV file: xf-goe447-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 447 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0581   0.10522   0.10124  -0.1160   0.9128   0.0496
 -10.000   0.0633   0.10317   0.09918  -0.1179   0.9046   0.0511
  -9.750   0.0525   0.10318   0.09914  -0.1232   0.8959   0.0518
  -9.500   0.0712   0.09841   0.09437  -0.1215   0.8907   0.0522
  -9.250   0.0854   0.09532   0.09125  -0.1209   0.8852   0.0528
  -9.000   0.0962   0.09287   0.08875  -0.1212   0.8803   0.0537
  -8.750   0.1054   0.09067   0.08655  -0.1220   0.8741   0.0547
  -8.500   0.1140   0.08844   0.08430  -0.1230   0.8682   0.0559
  -8.250   0.1220   0.08622   0.08203  -0.1245   0.8633   0.0574
  -8.000   0.1177   0.08540   0.08124  -0.1296   0.8544   0.0589
  -7.750   0.1183   0.08353   0.07935  -0.1364   0.8479   0.0592
  -7.500   0.1324   0.07979   0.07559  -0.1321   0.8450   0.0597
  -7.250   0.1475   0.07715   0.07295  -0.1304   0.8403   0.0604
  -7.000   0.1588   0.07509   0.07088  -0.1304   0.8355   0.0615
  -6.750   0.1712   0.07292   0.06868  -0.1319   0.8316   0.0629
  -6.500   0.1833   0.07075   0.06649  -0.1344   0.8271   0.0645
  -6.250   0.2060   0.06838   0.06402  -0.1501   0.8196   0.0676
  -6.000   0.2215   0.06465   0.06025  -0.1527   0.8158   0.0681
  -5.750   0.2345   0.06209   0.05767  -0.1507   0.8131   0.0686
  -5.500   0.2465   0.06023   0.05584  -0.1497   0.8087   0.0694
  -5.250   0.2616   0.05834   0.05396  -0.1501   0.8041   0.0704
  -5.000   0.2813   0.05617   0.05175  -0.1521   0.8004   0.0721
  -4.750   0.3312   0.05162   0.04679  -0.1677   0.7968   0.0781
  -4.500   0.3424   0.04940   0.04464  -0.1659   0.7926   0.0787
  -4.250   0.3566   0.04774   0.04301  -0.1649   0.7874   0.0796
  -4.000   0.3778   0.04588   0.04110  -0.1654   0.7834   0.0809
  -3.750   0.4053   0.04371   0.03882  -0.1675   0.7801   0.0834
  -3.500   0.4459   0.03966   0.03430  -0.1749   0.7754   0.0902
  -3.250   0.4628   0.03806   0.03276  -0.1740   0.7700   0.0913
  -3.000   0.4870   0.03653   0.03120  -0.1743   0.7661   0.0931
  -2.750   0.5253   0.03390   0.02807  -0.1782   0.7631   0.1039
  -2.500   0.5448   0.03264   0.02691  -0.1776   0.7588   0.1059
  -2.250   0.5791   0.02661   0.02001  -0.1797   0.7544   0.0751
  -2.000   0.6082   0.02444   0.01742  -0.1803   0.7508   0.0727
  -1.750   0.6392   0.02302   0.01565  -0.1809   0.7480   0.0738
  -1.500   0.6716   0.02225   0.01444  -0.1815   0.7456   0.0774
  -1.250   0.6936   0.02144   0.01355  -0.1808   0.7409   0.0800
  -1.000   0.7185   0.02103   0.01312  -0.1804   0.7363   0.0839
  -0.750   0.7484   0.02037   0.01222  -0.1806   0.7329   0.0907
  -0.500   0.7795   0.01986   0.01166  -0.1812   0.7301   0.1006
  -0.250   0.8061   0.01939   0.01119  -0.1810   0.7263   0.1099
   0.000   0.8281   0.01942   0.01119  -0.1801   0.7210   0.1183
   0.250   0.8560   0.01905   0.01087  -0.1802   0.7172   0.1282
   0.500   0.8868   0.01869   0.01048  -0.1807   0.7142   0.1378
   0.750   0.9168   0.01846   0.01025  -0.1811   0.7110   0.1447
   1.000   0.9362   0.01861   0.01045  -0.1796   0.7047   0.1494
   1.250   0.9646   0.01831   0.01021  -0.1797   0.7005   0.1552
   1.500   0.9965   0.01802   0.00989  -0.1803   0.6972   0.1632
   1.750   1.0208   0.01803   0.00999  -0.1798   0.6921   0.1749
   2.000   1.0446   0.01800   0.01010  -0.1791   0.6865   0.2009
   2.250   1.0737   0.01749   0.01006  -0.1794   0.6825   0.3765
   2.500   1.1054   0.01632   0.00980  -0.1797   0.6794   1.0000
   2.750   1.1226   0.01666   0.01015  -0.1778   0.6722   1.0000
   3.000   1.1511   0.01661   0.01000  -0.1778   0.6670   1.0000
   3.250   1.1851   0.01645   0.00967  -0.1788   0.6627   1.0000
   3.500   1.2019   0.01667   0.00994  -0.1768   0.6541   1.0000
   3.750   1.2334   0.01650   0.00964  -0.1773   0.6485   1.0000
   4.000   1.2546   0.01667   0.00981  -0.1761   0.6410   1.0000
   4.250   1.2811   0.01667   0.00976  -0.1758   0.6344   1.0000
   4.500   1.3091   0.01670   0.00973  -0.1758   0.6286   1.0000
   4.750   1.3290   0.01687   0.00991  -0.1744   0.6201   1.0000
   5.000   1.3605   0.01678   0.00971  -0.1750   0.6141   1.0000
   5.250   1.3762   0.01704   0.01004  -0.1729   0.6045   1.0000
   5.500   1.4068   0.01701   0.00990  -0.1733   0.5982   1.0000
   5.750   1.4216   0.01730   0.01027  -0.1710   0.5885   1.0000
   6.000   1.4506   0.01733   0.01020  -0.1713   0.5818   1.0000
   6.250   1.4647   0.01766   0.01062  -0.1689   0.5722   1.0000
   6.500   1.4914   0.01775   0.01064  -0.1688   0.5652   1.0000
   6.750   1.5054   0.01810   0.01106  -0.1664   0.5559   1.0000
   7.000   1.5297   0.01826   0.01117  -0.1658   0.5486   1.0000
   7.250   1.5428   0.01862   0.01159  -0.1633   0.5392   1.0000
   7.500   1.5646   0.01886   0.01179  -0.1624   0.5319   1.0000
   7.750   1.5771   0.01926   0.01227  -0.1598   0.5240   1.0000
   8.000   1.6017   0.01951   0.01245  -0.1594   0.5177   1.0000
   8.250   1.6108   0.02004   0.01308  -0.1563   0.5100   1.0000
   8.500   1.6330   0.02034   0.01335  -0.1555   0.5035   1.0000
   8.750   1.6443   0.02090   0.01400  -0.1530   0.4962   1.0000
   9.000   1.6616   0.02130   0.01439  -0.1514   0.4887   1.0000
   9.250   1.6713   0.02191   0.01506  -0.1487   0.4800   1.0000
   9.750   1.6902   0.02320   0.01637  -0.1433   0.4603   1.0000
  10.000   1.6994   0.02393   0.01710  -0.1407   0.4499   1.0000
  10.250   1.7096   0.02468   0.01782  -0.1383   0.4396   1.0000
  10.500   1.7123   0.02577   0.01901  -0.1351   0.4295   1.0000
  10.750   1.7201   0.02671   0.01993  -0.1326   0.4190   1.0000
  11.000   1.7235   0.02790   0.02115  -0.1297   0.4082   1.0000
  11.250   1.7257   0.02924   0.02260  -0.1269   0.3975   1.0000
  11.500   1.7294   0.03056   0.02392  -0.1243   0.3866   1.0000
  11.750   1.7295   0.03215   0.02556  -0.1215   0.3745   1.0000
  12.000   1.7278   0.03399   0.02749  -0.1188   0.3615   1.0000
  12.250   1.7262   0.03591   0.02948  -0.1162   0.3479   1.0000
  12.500   1.7236   0.03804   0.03164  -0.1138   0.3328   1.0000
  12.750   1.7192   0.04042   0.03405  -0.1113   0.3156   1.0000
  13.000   1.7117   0.04317   0.03676  -0.1088   0.2966   1.0000
  13.250   1.7026   0.04621   0.03973  -0.1064   0.2773   1.0000
  13.500   1.6935   0.04938   0.04283  -0.1042   0.2595   1.0000
  13.750   1.6856   0.05253   0.04593  -0.1022   0.2447   1.0000
  14.000   1.6781   0.05574   0.04910  -0.1003   0.2315   1.0000
  14.250   1.6697   0.05915   0.05247  -0.0986   0.2183   1.0000
  14.500   1.6615   0.06265   0.05594  -0.0971   0.2056   1.0000
  14.750   1.6529   0.06629   0.05959  -0.0957   0.1918   1.0000
  15.000   1.6422   0.07028   0.06356  -0.0944   0.1769   1.0000
  15.250   1.6293   0.07469   0.06795  -0.0934   0.1584   1.0000
  15.500   1.6123   0.07975   0.07292  -0.0924   0.1245   1.0000
  15.750   1.5825   0.08643   0.07928  -0.0916   0.0854   1.0000
  16.000   1.5590   0.09247   0.08519  -0.0909   0.0683   1.0000
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