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GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 449 AIRFOIL (goe449-il)
Reynolds number: 50,000
Max Cl/Cd: 12.09 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe449-il-50000-n5.txt
Download as CSV file: xf-goe449-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 449 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  -0.2257   0.11498   0.10775  -0.0732   0.9483   0.0901
  -9.750  -0.2225   0.11102   0.10378  -0.0760   0.9437   0.0899
  -9.500  -0.2192   0.10684   0.09959  -0.0793   0.9395   0.0901
  -9.250  -0.2265   0.10346   0.09626  -0.0799   0.9320   0.0898
  -9.000  -0.2283   0.09887   0.09167  -0.0832   0.9268   0.0892
  -8.750  -0.2392   0.09442   0.08723  -0.0853   0.9198   0.0884
  -8.500  -0.2588   0.08907   0.08191  -0.0882   0.9115   0.0875
  -8.250  -0.3074   0.08207   0.07486  -0.0904   0.9008   0.0859
  -8.000  -0.3438   0.07458   0.06712  -0.0922   0.8916   0.0850
  -7.750  -0.3615   0.07113   0.06352  -0.0900   0.8822   0.0851
  -7.500  -0.3564   0.06831   0.06056  -0.0898   0.8757   0.0861
  -7.250  -0.3530   0.06552   0.05760  -0.0892   0.8694   0.0873
  -7.000  -0.3577   0.06302   0.05492  -0.0869   0.8609   0.0885
  -6.750  -0.3482   0.05951   0.05105  -0.0872   0.8558   0.0904
  -6.500  -0.3524   0.05705   0.04827  -0.0843   0.8474   0.0915
  -6.250  -0.3435   0.05394   0.04469  -0.0833   0.8411   0.0929
  -6.000  -0.3247   0.05053   0.04058  -0.0836   0.8370   0.0951
  -5.750  -0.3207   0.04972   0.03973  -0.0805   0.8282   0.0968
  -5.500  -0.2978   0.04856   0.03847  -0.0803   0.8228   0.0997
  -5.250  -0.2689   0.04676   0.03630  -0.0811   0.8191   0.1039
  -5.000  -0.2647   0.04571   0.03489  -0.0778   0.8097   0.1064
  -4.750  -0.2392   0.04455   0.03358  -0.0778   0.8047   0.1103
  -4.500  -0.2065   0.04347   0.03233  -0.0788   0.8012   0.1162
  -4.250  -0.2003   0.04301   0.03159  -0.0757   0.7914   0.1203
  -4.000  -0.1726   0.04221   0.03076  -0.0759   0.7865   0.1262
  -3.750  -0.1380   0.04128   0.02957  -0.0769   0.7833   0.1348
  -3.500  -0.1326   0.04126   0.02954  -0.0737   0.7730   0.1394
  -3.250  -0.1027   0.04065   0.02884  -0.0741   0.7683   0.1486
  -3.000  -0.0670   0.03991   0.02805  -0.0752   0.7653   0.1593
  -2.750  -0.0631   0.04021   0.02826  -0.0719   0.7545   0.1661
  -2.500  -0.0315   0.03970   0.02774  -0.0724   0.7502   0.1781
  -2.250  -0.0049   0.03944   0.02742  -0.0723   0.7449   0.1911
  -2.000   0.0098   0.03961   0.02753  -0.0707   0.7362   0.2031
  -1.750   0.0413   0.03919   0.02712  -0.0712   0.7322   0.2217
  -1.500   0.0589   0.03925   0.02722  -0.0699   0.7255   0.2394
  -1.250   0.0757   0.03930   0.02735  -0.0685   0.7180   0.2627
  -1.000   0.1055   0.03877   0.02700  -0.0688   0.7143   0.3034
  -0.750   0.1163   0.03891   0.02743  -0.0667   0.7066   0.3496
  -0.500   0.1316   0.03866   0.02770  -0.0650   0.7002   0.4495
  -0.250   0.2025   0.03773   0.02834  -0.0707   0.6980   0.8989
   0.250   0.2754   0.03914   0.02923  -0.0759   0.6855   1.0000
   0.500   0.2974   0.03936   0.02921  -0.0750   0.6806   1.0000
   0.750   0.3273   0.03932   0.02893  -0.0751   0.6776   1.0000
   1.000   0.3170   0.04078   0.03029  -0.0706   0.6663   1.0000
   1.250   0.3433   0.04092   0.03024  -0.0703   0.6623   1.0000
   1.750   0.3629   0.04264   0.03169  -0.0661   0.6479   1.0000
   2.000   0.3915   0.04274   0.03163  -0.0661   0.6445   1.0000
   2.250   0.3897   0.04425   0.03306  -0.0630   0.6352   1.0000
   2.500   0.4107   0.04473   0.03341  -0.0622   0.6300   1.0000
   2.750   0.4409   0.04476   0.03331  -0.0623   0.6269   1.0000
   3.000   0.4355   0.04660   0.03510  -0.0592   0.6166   1.0000
   3.250   0.4601   0.04694   0.03534  -0.0588   0.6122   1.0000
   3.500   0.4917   0.04690   0.03519  -0.0590   0.6094   1.0000
   3.750   0.4834   0.04905   0.03731  -0.0558   0.5982   1.0000
   4.000   0.5110   0.04923   0.03741  -0.0557   0.5944   1.0000
   4.500   0.5328   0.05154   0.03963  -0.0528   0.5798   1.0000
   4.750   0.5635   0.05151   0.03954  -0.0528   0.5765   1.0000
   5.000   0.5590   0.05369   0.04171  -0.0504   0.5657   1.0000
   5.250   0.5844   0.05397   0.04195  -0.0500   0.5611   1.0000
   5.500   0.6175   0.05372   0.04164  -0.0502   0.5583   1.0000
   5.750   0.6078   0.05636   0.04430  -0.0476   0.5459   1.0000
   6.000   0.6379   0.05628   0.04419  -0.0475   0.5423   1.0000
   6.500   0.6593   0.05884   0.04674  -0.0450   0.5262   1.0000
   6.750   0.6927   0.05840   0.04629  -0.0450   0.5232   1.0000
   7.000   0.6817   0.06140   0.04932  -0.0427   0.5101   1.0000
   7.250   0.7125   0.06113   0.04905  -0.0425   0.5065   1.0000
   7.750   0.7327   0.06390   0.05185  -0.0403   0.4896   1.0000
   8.000   0.7656   0.06335   0.05131  -0.0401   0.4869   1.0000
   8.250   0.7514   0.06694   0.05496  -0.0382   0.4728   1.0000
   8.500   0.7832   0.06640   0.05444  -0.0379   0.4697   1.0000
   8.750   0.7699   0.07009   0.05817  -0.0363   0.4560   1.0000
   9.000   0.7999   0.06968   0.05781  -0.0359   0.4526   1.0000
   9.250   0.7878   0.07339   0.06157  -0.0346   0.4394   1.0000
   9.500   0.8165   0.07304   0.06126  -0.0341   0.4357   1.0000
  10.000   0.8326   0.07654   0.06486  -0.0325   0.4189   1.0000
  10.500   0.8479   0.08026   0.06870  -0.0311   0.4024   1.0000
  11.000   0.8636   0.08394   0.07249  -0.0299   0.3859   1.0000
  11.500   0.8801   0.08750   0.07618  -0.0287   0.3696   1.0000
  12.000   0.8982   0.09075   0.07955  -0.0276   0.3532   1.0000
  12.500   0.9152   0.09414   0.08309  -0.0267   0.3370   1.0000
  13.000   0.9290   0.09811   0.08719  -0.0260   0.3208   1.0000
  13.500   0.9394   0.10276   0.09198  -0.0258   0.3048   1.0000
  14.000   0.9458   0.10818   0.09756  -0.0259   0.2888   1.0000
  14.250   0.9732   0.10703   0.09647  -0.0249   0.2860   1.0000
  14.750   0.9374   0.11975   0.10934  -0.0277   0.2635   1.0000
  15.000   0.9480   0.12140   0.11107  -0.0277   0.2574   1.0000
  15.250   0.9728   0.12056   0.11032  -0.0268   0.2545   1.0000
  15.750   0.9623   0.12968   0.11958  -0.0291   0.2391   1.0000
  16.250   0.9505   0.13929   0.12931  -0.0321   0.2246   1.0000
  17.250   0.9774   0.14927   0.13958  -0.0347   0.2055   1.0000
  17.750   0.9584   0.16074   0.15115  -0.0396   0.1923   1.0000
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