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GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 409 AIRFOIL (goe409-il)
Reynolds number: 200,000
Max Cl/Cd: 40.85 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe409-il-200000.txt
Download as CSV file: xf-goe409-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 409 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7160   0.09697   0.09307  -0.0392   1.0000   0.0781
 -13.000  -0.6954   0.09645   0.09256  -0.0360   1.0000   0.0790
 -12.750  -0.9504   0.05504   0.04995  -0.0536   1.0000   0.0483
 -12.500  -0.9580   0.05291   0.04771  -0.0517   1.0000   0.0495
 -12.250  -0.9746   0.05033   0.04493  -0.0486   1.0000   0.0500
 -12.000  -0.9889   0.04855   0.04296  -0.0446   1.0000   0.0513
 -11.750  -1.0062   0.04668   0.04085  -0.0394   1.0000   0.0523
 -11.500  -1.0193   0.04546   0.03931  -0.0343   1.0000   0.0536
 -11.250  -1.0314   0.04475   0.03826  -0.0289   1.0000   0.0546
 -11.000  -1.0257   0.04023   0.03369  -0.0276   1.0000   0.0569
 -10.750  -1.0104   0.03892   0.03242  -0.0263   1.0000   0.0591
 -10.500  -1.0048   0.03771   0.03107  -0.0232   1.0000   0.0614
 -10.250  -1.0021   0.03657   0.02967  -0.0195   1.0000   0.0632
 -10.000  -1.0000   0.03608   0.02890  -0.0152   1.0000   0.0648
  -9.750  -0.9947   0.03324   0.02580  -0.0123   1.0000   0.0667
  -9.500  -0.9796   0.03141   0.02397  -0.0109   1.0000   0.0690
  -9.250  -0.9657   0.03031   0.02282  -0.0088   1.0000   0.0711
  -9.000  -0.9528   0.02933   0.02172  -0.0064   1.0000   0.0732
  -8.750  -0.9399   0.02844   0.02065  -0.0039   1.0000   0.0750
  -8.500  -0.9268   0.02774   0.01976  -0.0014   1.0000   0.0765
  -8.250  -0.9126   0.02709   0.01893   0.0010   1.0000   0.0773
  -8.000  -0.8912   0.02504   0.01679   0.0018   1.0000   0.0787
  -7.750  -0.8708   0.02374   0.01546   0.0029   1.0000   0.0802
  -7.500  -0.8517   0.02280   0.01450   0.0043   1.0000   0.0812
  -7.250  -0.8334   0.02200   0.01366   0.0060   1.0000   0.0821
  -7.000  -0.8157   0.02126   0.01290   0.0077   1.0000   0.0832
  -6.750  -0.7987   0.02061   0.01222   0.0096   1.0000   0.0844
  -6.500  -0.7823   0.02001   0.01159   0.0115   1.0000   0.0858
  -6.250  -0.7661   0.01945   0.01100   0.0136   1.0000   0.0869
  -6.000  -0.7503   0.01892   0.01043   0.0156   1.0000   0.0879
  -5.750  -0.7346   0.01844   0.00991   0.0177   1.0000   0.0889
  -5.500  -0.7190   0.01799   0.00942   0.0198   1.0000   0.0898
  -5.250  -0.7049   0.01742   0.00887   0.0221   1.0000   0.0914
  -5.000  -0.6903   0.01692   0.00839   0.0243   1.0000   0.0934
  -4.750  -0.6747   0.01652   0.00799   0.0263   1.0000   0.0963
  -4.500  -0.6525   0.01619   0.00765   0.0270   0.9988   0.1001
  -4.250  -0.6154   0.01588   0.00741   0.0246   0.9943   0.1076
  -4.000  -0.5810   0.01548   0.00718   0.0228   0.9892   0.1290
  -3.750  -0.5464   0.01486   0.00695   0.0208   0.9841   0.1980
  -3.500  -0.5187   0.01396   0.00667   0.0200   0.9777   0.3121
  -3.250  -0.4888   0.01328   0.00665   0.0190   0.9718   0.4526
  -3.000  -0.4586   0.01301   0.00663   0.0183   0.9652   0.5186
  -2.750  -0.4243   0.01279   0.00662   0.0169   0.9592   0.5670
  -2.500  -0.3896   0.01261   0.00662   0.0156   0.9534   0.6093
  -2.250  -0.3577   0.01243   0.00662   0.0149   0.9461   0.6526
  -2.000  -0.3167   0.01231   0.00665   0.0125   0.9423   0.6917
  -1.750  -0.2891   0.01221   0.00668   0.0129   0.9333   0.7260
  -1.500  -0.2474   0.01213   0.00674   0.0106   0.9288   0.7619
  -1.250  -0.2119   0.01213   0.00685   0.0096   0.9221   0.7922
  -1.000  -0.1729   0.01219   0.00698   0.0080   0.9159   0.8200
  -0.750  -0.1264   0.01232   0.00716   0.0051   0.9126   0.8460
  -0.500  -0.0916   0.01252   0.00741   0.0048   0.9039   0.8656
  -0.250  -0.0457   0.01266   0.00756   0.0024   0.8981   0.8809
   0.000   0.0000   0.01275   0.00766   0.0000   0.8895   0.8896
   0.250   0.0455   0.01267   0.00757  -0.0024   0.8810   0.8981
   0.500   0.0913   0.01252   0.00741  -0.0048   0.8658   0.9039
   0.750   0.1262   0.01232   0.00716  -0.0051   0.8457   0.9126
   1.000   0.1729   0.01219   0.00698  -0.0080   0.8200   0.9160
   1.250   0.2118   0.01213   0.00684  -0.0095   0.7922   0.9221
   1.500   0.2473   0.01213   0.00674  -0.0105   0.7617   0.9288
   1.750   0.2892   0.01220   0.00669  -0.0129   0.7270   0.9333
   2.000   0.3167   0.01231   0.00665  -0.0125   0.6917   0.9423
   2.250   0.3577   0.01243   0.00662  -0.0149   0.6527   0.9461
   2.500   0.3895   0.01261   0.00662  -0.0156   0.6095   0.9534
   2.750   0.4240   0.01278   0.00661  -0.0169   0.5670   0.9592
   3.000   0.4586   0.01300   0.00663  -0.0183   0.5198   0.9653
   3.250   0.4887   0.01329   0.00664  -0.0189   0.4495   0.9719
   3.500   0.5186   0.01394   0.00666  -0.0200   0.3146   0.9777
   3.750   0.5465   0.01485   0.00694  -0.0208   0.1989   0.9841
   4.000   0.5811   0.01547   0.00717  -0.0229   0.1295   0.9892
   4.250   0.6154   0.01587   0.00740  -0.0246   0.1078   0.9943
   4.500   0.6526   0.01619   0.00765  -0.0270   0.1001   0.9989
   4.750   0.6745   0.01651   0.00799  -0.0263   0.0962   1.0000
   5.000   0.6901   0.01692   0.00839  -0.0243   0.0934   1.0000
   5.250   0.7046   0.01742   0.00887  -0.0221   0.0914   1.0000
   5.500   0.7188   0.01799   0.00942  -0.0198   0.0898   1.0000
   5.750   0.7345   0.01843   0.00990  -0.0177   0.0889   1.0000
   6.000   0.7501   0.01891   0.01042  -0.0156   0.0879   1.0000
   6.250   0.7659   0.01945   0.01099  -0.0135   0.0870   1.0000
   6.500   0.7821   0.02001   0.01159  -0.0115   0.0858   1.0000
   6.750   0.7986   0.02060   0.01221  -0.0096   0.0845   1.0000
   7.000   0.8155   0.02125   0.01289  -0.0077   0.0831   1.0000
   7.250   0.8332   0.02198   0.01365  -0.0059   0.0821   1.0000
   7.500   0.8516   0.02279   0.01449  -0.0043   0.0812   1.0000
   7.750   0.8706   0.02372   0.01545  -0.0029   0.0802   1.0000
   8.000   0.8909   0.02498   0.01673  -0.0017   0.0788   1.0000
   8.250   0.9126   0.02710   0.01894  -0.0010   0.0773   1.0000
   8.500   0.9266   0.02771   0.01973   0.0014   0.0765   1.0000
   8.750   0.9397   0.02843   0.02064   0.0040   0.0750   1.0000
   9.000   0.9526   0.02933   0.02172   0.0065   0.0732   1.0000
   9.250   0.9656   0.03030   0.02281   0.0088   0.0711   1.0000
   9.500   0.9795   0.03140   0.02396   0.0109   0.0689   1.0000
   9.750   0.9948   0.03331   0.02586   0.0123   0.0665   1.0000
  10.000   0.9999   0.03606   0.02888   0.0153   0.0648   1.0000
  10.250   1.0020   0.03659   0.02969   0.0195   0.0633   1.0000
  10.500   1.0048   0.03771   0.03106   0.0232   0.0613   1.0000
  10.750   1.0104   0.03893   0.03243   0.0263   0.0591   1.0000
  11.000   1.0257   0.04025   0.03372   0.0276   0.0570   1.0000
  11.500   1.0185   0.04537   0.03923   0.0345   0.0535   1.0000
  11.750   1.0059   0.04674   0.04091   0.0395   0.0522   1.0000
  12.000   0.9896   0.04849   0.04290   0.0445   0.0512   1.0000
  12.250   0.9744   0.05044   0.04505   0.0486   0.0501   1.0000
  12.500   0.9635   0.05250   0.04725   0.0513   0.0489   1.0000
  12.750   0.9503   0.05514   0.05005   0.0535   0.0483   1.0000
  13.000   0.9867   0.05605   0.05070   0.0526   0.0460   1.0000
  13.500   0.9393   0.06506   0.06006   0.0551   0.0453   1.0000
  13.750   0.9122   0.06960   0.06481   0.0549   0.0453   1.0000
  14.000   0.8831   0.07495   0.07032   0.0533   0.0453   1.0000
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