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GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 447 AIRFOIL (goe447-il)
Reynolds number: 500,000
Max Cl/Cd: 116.17 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe447-il-500000-n5.txt
Download as CSV file: xf-goe447-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0264   0.09762   0.09401  -0.1057   0.7685   0.0242
  -9.750   0.0334   0.09463   0.09099  -0.1071   0.7648   0.0239
  -9.500   0.0406   0.09170   0.08803  -0.1086   0.7614   0.0237
  -9.250   0.0484   0.08885   0.08519  -0.1102   0.7579   0.0238
  -9.000   0.0567   0.08616   0.08249  -0.1117   0.7541   0.0239
  -8.750   0.0655   0.08360   0.07992  -0.1132   0.7502   0.0245
  -8.500   0.0733   0.08083   0.07712  -0.1148   0.7465   0.0249
  -7.000   0.0892   0.02102   0.01588  -0.1767   0.7244   0.0272
  -6.750   0.1141   0.01917   0.01374  -0.1777   0.7211   0.0274
  -6.500   0.1399   0.01792   0.01224  -0.1782   0.7178   0.0277
  -6.250   0.1662   0.01693   0.01104  -0.1785   0.7147   0.0280
  -5.750   0.2199   0.01540   0.00915  -0.1790   0.7081   0.0285
  -5.500   0.2471   0.01478   0.00838  -0.1792   0.7038   0.0288
  -5.250   0.2743   0.01425   0.00769  -0.1793   0.6994   0.0292
  -5.000   0.3017   0.01381   0.00709  -0.1793   0.6956   0.0295
  -4.750   0.3294   0.01339   0.00657  -0.1795   0.6922   0.0298
  -4.500   0.3573   0.01302   0.00612  -0.1796   0.6885   0.0301
  -4.250   0.3851   0.01273   0.00573  -0.1796   0.6849   0.0304
  -4.000   0.4127   0.01238   0.00530  -0.1797   0.6812   0.0310
  -3.750   0.4404   0.01210   0.00497  -0.1798   0.6777   0.0316
  -3.500   0.4683   0.01186   0.00471  -0.1799   0.6738   0.0322
  -3.250   0.4962   0.01166   0.00446  -0.1799   0.6698   0.0328
  -3.000   0.5240   0.01148   0.00423  -0.1800   0.6660   0.0334
  -2.500   0.5798   0.01119   0.00384  -0.1801   0.6586   0.0348
  -2.250   0.6077   0.01106   0.00368  -0.1801   0.6545   0.0355
  -2.000   0.6355   0.01092   0.00352  -0.1801   0.6508   0.0369
  -1.750   0.6632   0.01083   0.00340  -0.1801   0.6473   0.0385
  -1.250   0.7189   0.01066   0.00326  -0.1803   0.6404   0.0456
  -1.000   0.7467   0.01065   0.00330  -0.1803   0.6369   0.0538
  -0.750   0.7743   0.01068   0.00332  -0.1803   0.6334   0.0607
  -0.500   0.8018   0.01074   0.00335  -0.1802   0.6300   0.0655
  -0.250   0.8295   0.01075   0.00336  -0.1803   0.6267   0.0686
   0.000   0.8570   0.01076   0.00339  -0.1803   0.6229   0.0715
   0.250   0.8843   0.01078   0.00341  -0.1802   0.6188   0.0745
   0.500   0.9111   0.01084   0.00343  -0.1801   0.6146   0.0772
   0.750   0.9382   0.01080   0.00342  -0.1801   0.6105   0.0806
   1.000   0.9651   0.01081   0.00344  -0.1800   0.6055   0.0831
   1.250   0.9911   0.01084   0.00346  -0.1797   0.5993   0.0855
   1.500   1.0171   0.01089   0.00348  -0.1794   0.5927   0.0873
   1.750   1.0429   0.01091   0.00350  -0.1791   0.5853   0.0891
   2.000   1.0683   0.01095   0.00353  -0.1787   0.5792   0.0910
   2.250   1.0946   0.01098   0.00359  -0.1786   0.5731   0.0934
   2.500   1.1197   0.01105   0.00365  -0.1781   0.5665   0.0959
   2.750   1.1450   0.01113   0.00373  -0.1777   0.5597   0.0983
   3.000   1.1690   0.01124   0.00382  -0.1771   0.5503   0.1009
   3.250   1.1926   0.01135   0.00393  -0.1764   0.5396   0.1081
   3.500   1.2150   0.01147   0.00408  -0.1755   0.5283   0.1312
   3.750   1.2374   0.01150   0.00434  -0.1748   0.5170   0.2635
   4.000   1.2594   0.01163   0.00456  -0.1739   0.5054   0.3221
   4.250   1.2802   0.01171   0.00483  -0.1728   0.4933   0.4393
   4.500   1.2941   0.01114   0.00517  -0.1701   0.4811   1.0000
   5.000   1.3272   0.01185   0.00574  -0.1661   0.4569   1.0000
   5.250   1.3448   0.01222   0.00605  -0.1644   0.4481   1.0000
   5.500   1.3631   0.01259   0.00638  -0.1628   0.4398   1.0000
   5.750   1.3810   0.01297   0.00673  -0.1613   0.4329   1.0000
   6.000   1.4002   0.01333   0.00707  -0.1599   0.4262   1.0000
   6.500   1.4354   0.01419   0.00790  -0.1569   0.4121   1.0000
   6.750   1.4513   0.01471   0.00838  -0.1551   0.4042   1.0000
   7.000   1.4690   0.01517   0.00884  -0.1537   0.3974   1.0000
   7.250   1.4865   0.01564   0.00932  -0.1523   0.3907   1.0000
   7.500   1.5025   0.01621   0.00987  -0.1507   0.3854   1.0000
   7.750   1.5216   0.01664   0.01034  -0.1496   0.3807   1.0000
   8.000   1.5387   0.01718   0.01090  -0.1483   0.3741   1.0000
   8.250   1.5526   0.01790   0.01161  -0.1466   0.3656   1.0000
   8.500   1.5661   0.01867   0.01236  -0.1448   0.3542   1.0000
   8.750   1.5787   0.01952   0.01319  -0.1431   0.3414   1.0000
   9.000   1.5886   0.02056   0.01419  -0.1410   0.3260   1.0000
   9.250   1.5934   0.02197   0.01551  -0.1384   0.3046   1.0000
   9.500   1.5931   0.02380   0.01721  -0.1354   0.2764   1.0000
   9.750   1.5879   0.02603   0.01928  -0.1320   0.2467   1.0000
  10.000   1.5857   0.02813   0.02126  -0.1290   0.2241   1.0000
  10.250   1.5869   0.03005   0.02310  -0.1266   0.2075   1.0000
  10.500   1.5904   0.03183   0.02484  -0.1245   0.1956   1.0000
  10.750   1.5951   0.03358   0.02657  -0.1226   0.1860   1.0000
  11.000   1.6032   0.03508   0.02809  -0.1210   0.1792   1.0000
  11.250   1.6095   0.03675   0.02976  -0.1194   0.1727   1.0000
  11.500   1.6165   0.03839   0.03142  -0.1179   0.1666   1.0000
  11.750   1.6231   0.04010   0.03315  -0.1165   0.1599   1.0000
  12.000   1.6279   0.04201   0.03506  -0.1149   0.1538   1.0000
  12.250   1.6360   0.04365   0.03674  -0.1137   0.1471   1.0000
  12.500   1.6391   0.04576   0.03885  -0.1122   0.1383   1.0000
  12.750   1.6385   0.04826   0.04128  -0.1105   0.1189   1.0000
  13.000   1.6173   0.05286   0.04564  -0.1077   0.0821   1.0000
  13.250   1.6118   0.05602   0.04878  -0.1060   0.0710   1.0000
  13.500   1.6074   0.05914   0.05189  -0.1045   0.0570   1.0000
  13.750   1.5903   0.06370   0.05632  -0.1025   0.0335   1.0000
  14.000   1.5861   0.06698   0.05961  -0.1013   0.0270   1.0000
  14.250   1.5856   0.06985   0.06254  -0.1003   0.0238   1.0000
  14.500   1.5864   0.07265   0.06539  -0.0995   0.0217   1.0000
  14.750   1.5868   0.07551   0.06831  -0.0987   0.0201   1.0000
  15.000   1.5874   0.07839   0.07125  -0.0981   0.0189   1.0000
  15.250   1.5887   0.08123   0.07417  -0.0975   0.0180   1.0000
  15.500   1.5894   0.08413   0.07715  -0.0970   0.0172   1.0000
  15.750   1.5884   0.08728   0.08037  -0.0965   0.0165   1.0000
  16.000   1.5869   0.09054   0.08370  -0.0961   0.0159   1.0000
  16.250   1.5861   0.09374   0.08698  -0.0958   0.0155   1.0000
  16.500   1.5857   0.09693   0.09026  -0.0956   0.0150   1.0000
  16.750   1.5852   0.10014   0.09357  -0.0955   0.0146   1.0000
  17.000   1.5833   0.10356   0.09707  -0.0955   0.0141   1.0000
  17.250   1.5811   0.10704   0.10063  -0.0956   0.0137   1.0000
  17.500   1.5783   0.11064   0.10430  -0.0958   0.0133   1.0000
  17.750   1.5742   0.11447   0.10822  -0.0961   0.0130   1.0000
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