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GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 429 AIRFOIL (goe429-il)
Reynolds number: 50,000
Max Cl/Cd: 23.14 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe429-il-50000.txt
Download as CSV file: xf-goe429-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 429 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.8355   0.08282   0.07594   0.0086   1.0000   0.1842
  -9.500  -0.8574   0.07452   0.06759   0.0040   1.0000   0.1829
  -9.250  -0.8830   0.06583   0.05872  -0.0005   1.0000   0.1817
  -9.000  -0.9031   0.05782   0.05026  -0.0038   1.0000   0.1823
  -8.500  -0.8874   0.04959   0.04144  -0.0046   1.0000   0.1966
  -8.250  -0.8717   0.04646   0.03812  -0.0045   1.0000   0.2052
  -8.000  -0.8595   0.04259   0.03367  -0.0050   1.0000   0.2141
  -7.750  -0.8366   0.04061   0.03172  -0.0045   1.0000   0.2246
  -7.500  -0.8170   0.03784   0.02863  -0.0045   1.0000   0.2352
  -7.250  -0.7957   0.03541   0.02583  -0.0045   1.0000   0.2477
  -7.000  -0.7721   0.03354   0.02380  -0.0042   1.0000   0.2619
  -6.750  -0.7475   0.03182   0.02202  -0.0039   1.0000   0.2773
  -6.500  -0.7226   0.03037   0.02062  -0.0034   1.0000   0.2956
  -6.250  -0.6973   0.02915   0.01950  -0.0026   1.0000   0.3165
  -6.000  -0.6728   0.02797   0.01836  -0.0019   1.0000   0.3443
  -5.750  -0.6482   0.02707   0.01760  -0.0008   1.0000   0.3766
  -5.500  -0.6240   0.02652   0.01721   0.0007   1.0000   0.4116
  -5.250  -0.5998   0.02608   0.01689   0.0023   1.0000   0.4455
  -5.000  -0.5755   0.02578   0.01667   0.0040   1.0000   0.4767
  -4.750  -0.5513   0.02546   0.01641   0.0056   1.0000   0.5058
  -4.500  -0.5271   0.02517   0.01611   0.0070   1.0000   0.5347
  -4.250  -0.5034   0.02532   0.01640   0.0096   1.0000   0.5589
  -4.000  -0.4807   0.02545   0.01660   0.0121   1.0000   0.5871
  -3.750  -0.4584   0.02544   0.01662   0.0144   1.0000   0.6160
  -3.500  -0.4361   0.02537   0.01662   0.0170   1.0000   0.6397
  -3.250  -0.4135   0.02478   0.01601   0.0182   1.0000   0.6652
  -3.000  -0.3916   0.02435   0.01560   0.0202   1.0000   0.6874
  -2.750  -0.3706   0.02371   0.01495   0.0214   1.0000   0.7129
  -2.500  -0.3510   0.02323   0.01452   0.0237   1.0000   0.7350
  -2.250  -0.3333   0.02261   0.01391   0.0253   1.0000   0.7605
  -2.000  -0.3168   0.02214   0.01348   0.0279   1.0000   0.7826
  -1.750  -0.3022   0.02160   0.01295   0.0300   1.0000   0.8084
  -1.500  -0.2856   0.02118   0.01258   0.0324   1.0000   0.8323
  -1.250  -0.2685   0.02076   0.01216   0.0341   1.0000   0.8596
  -1.000  -0.2439   0.02046   0.01187   0.0347   1.0000   0.8888
  -0.750  -0.1994   0.02035   0.01176   0.0316   1.0000   0.9200
  -0.500  -0.1197   0.02040   0.01178   0.0219   1.0000   0.9515
  -0.250  -0.0222   0.02026   0.01164   0.0079   1.0000   0.9793
   0.000   0.0357   0.02001   0.01143  -0.0008   1.0000   1.0000
   0.250   0.0032   0.01992   0.01134   0.0045   1.0000   1.0000
   0.500  -0.0276   0.01968   0.01109   0.0096   1.0000   1.0000
   0.750   0.0717   0.02020   0.01167  -0.0055   0.9702   1.0000
   1.000   0.1953   0.02027   0.01192  -0.0224   0.9308   1.0000
   1.250   0.2556   0.02024   0.01197  -0.0273   0.8876   1.0000
   1.500   0.2787   0.02034   0.01210  -0.0254   0.8467   1.0000
   1.750   0.2902   0.02048   0.01221  -0.0216   0.8067   1.0000
   2.000   0.3005   0.02057   0.01223  -0.0172   0.7679   1.0000
   2.250   0.3126   0.02063   0.01216  -0.0128   0.7303   1.0000
   2.500   0.3279   0.02080   0.01221  -0.0093   0.6863   1.0000
   2.750   0.3461   0.02095   0.01219  -0.0062   0.6430   1.0000
   3.000   0.3668   0.02110   0.01214  -0.0035   0.6012   1.0000
   3.250   0.3897   0.02139   0.01226  -0.0018   0.5606   1.0000
   3.500   0.4141   0.02180   0.01249  -0.0004   0.5259   1.0000
   3.750   0.4394   0.02235   0.01287   0.0006   0.4965   1.0000
   4.000   0.4654   0.02302   0.01340   0.0013   0.4724   1.0000
   4.250   0.4922   0.02389   0.01418   0.0016   0.4530   1.0000
   4.500   0.5193   0.02491   0.01522   0.0017   0.4354   1.0000
   4.750   0.5462   0.02594   0.01625   0.0018   0.4202   1.0000
   5.000   0.5731   0.02703   0.01740   0.0019   0.4065   1.0000
   5.250   0.5994   0.02813   0.01859   0.0020   0.3913   1.0000
   5.500   0.6245   0.02889   0.01930   0.0026   0.3724   1.0000
   5.750   0.6487   0.02955   0.02006   0.0032   0.3491   1.0000
   6.000   0.6732   0.03000   0.02040   0.0042   0.3274   1.0000
   6.250   0.6969   0.03066   0.02110   0.0049   0.3036   1.0000
   6.500   0.7209   0.03115   0.02146   0.0060   0.2777   1.0000
   6.750   0.7434   0.03225   0.02247   0.0070   0.2443   1.0000
   7.000   0.7640   0.03418   0.02447   0.0078   0.2083   1.0000
   7.250   0.7860   0.03626   0.02660   0.0084   0.1870   1.0000
   7.500   0.8068   0.03916   0.02979   0.0087   0.1748   1.0000
   7.750   0.8287   0.04149   0.03214   0.0091   0.1659   1.0000
   8.000   0.8434   0.04511   0.03631   0.0089   0.1582   1.0000
   8.250   0.8655   0.04724   0.03833   0.0094   0.1521   1.0000
   8.500   0.8692   0.05280   0.04459   0.0085   0.1499   1.0000
   8.750   0.8663   0.05899   0.05129   0.0071   0.1491   1.0000
   9.000   0.8538   0.06603   0.05870   0.0046   0.1497   1.0000
   9.250   0.8372   0.07335   0.06622   0.0015   0.1509   1.0000
   9.500   0.8242   0.08026   0.07321  -0.0017   0.1521   1.0000
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