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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 200,000
Max Cl/Cd: 84.02 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610b-il-200000-n5.txt
Download as CSV file: xf-goe610b-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2876   0.10405   0.10058  -0.0358   1.0000   0.0175
  -9.000  -0.2868   0.10131   0.09789  -0.0357   1.0000   0.0173
  -8.750  -0.2873   0.09879   0.09542  -0.0355   1.0000   0.0173
  -8.500  -0.2832   0.09563   0.09231  -0.0372   0.9977   0.0178
  -8.250  -0.2693   0.09146   0.08813  -0.0417   0.9874   0.0179
  -8.000  -0.2567   0.08700   0.08368  -0.0472   0.9753   0.0184
  -7.750  -0.2422   0.08271   0.07940  -0.0521   0.9632   0.0183
  -7.500  -0.2245   0.07807   0.07473  -0.0582   0.9506   0.0184
  -7.250  -0.2046   0.07295   0.06958  -0.0655   0.9372   0.0186
  -7.000  -0.1804   0.06742   0.06398  -0.0742   0.9236   0.0193
  -6.750  -0.1598   0.06424   0.06078  -0.0779   0.9127   0.0205
  -6.500  -0.1350   0.06191   0.05838  -0.0813   0.9025   0.0217
  -6.000  -0.0888   0.05407   0.05033  -0.0910   0.8794   0.0231
  -5.750  -0.0663   0.05047   0.04658  -0.0948   0.8687   0.0246
  -5.500  -0.0426   0.04633   0.04225  -0.0988   0.8591   0.0269
  -5.250  -0.0185   0.04042   0.03602  -0.1030   0.8496   0.0287
  -5.000   0.0043   0.03551   0.03078  -0.1051   0.8407   0.0313
  -4.500   0.0492   0.03356   0.02861  -0.1052   0.8238   0.0347
  -4.250   0.0732   0.03116   0.02594  -0.1056   0.8160   0.0377
  -4.000   0.0973   0.02746   0.02176  -0.1057   0.8076   0.0411
  -3.750   0.1203   0.02436   0.01815  -0.1053   0.8000   0.0440
  -3.500   0.1440   0.02416   0.01795  -0.1050   0.7914   0.0458
  -3.250   0.1680   0.02284   0.01639  -0.1046   0.7831   0.0477
  -3.000   0.1924   0.02114   0.01433  -0.1040   0.7748   0.0487
  -2.750   0.2169   0.01970   0.01255  -0.1033   0.7658   0.0498
  -2.500   0.2424   0.01859   0.01107  -0.1027   0.7574   0.0516
  -2.250   0.2674   0.01753   0.00976  -0.1020   0.7475   0.0515
  -2.000   0.2930   0.01662   0.00859  -0.1014   0.7380   0.0514
  -1.750   0.3189   0.01585   0.00758  -0.1009   0.7283   0.0516
  -1.500   0.3447   0.01523   0.00676  -0.1003   0.7173   0.0520
  -1.250   0.3708   0.01475   0.00608  -0.0998   0.7067   0.0528
  -1.000   0.3967   0.01416   0.00538  -0.0993   0.6964   0.0539
  -0.750   0.4222   0.01370   0.00487  -0.0987   0.6851   0.0554
  -0.500   0.4476   0.01340   0.00450  -0.0982   0.6728   0.0571
  -0.250   0.4729   0.01317   0.00418  -0.0975   0.6600   0.0586
   0.000   0.4981   0.01298   0.00391  -0.0969   0.6480   0.0598
   0.250   0.5233   0.01285   0.00369  -0.0963   0.6364   0.0608
   0.500   0.5487   0.01277   0.00354  -0.0957   0.6269   0.0621
   0.750   0.5735   0.01259   0.00337  -0.0951   0.6172   0.0651
   1.000   0.5988   0.01254   0.00328  -0.0946   0.6085   0.0669
   1.250   0.6243   0.01248   0.00321  -0.0940   0.6007   0.0674
   1.500   0.6497   0.01248   0.00315  -0.0935   0.5936   0.0679
   1.750   0.6752   0.01248   0.00314  -0.0930   0.5853   0.0686
   2.000   0.7006   0.01252   0.00313  -0.0924   0.5779   0.0697
   2.250   0.7262   0.01255   0.00317  -0.0920   0.5708   0.0711
   2.500   0.7519   0.01260   0.00324  -0.0915   0.5654   0.0742
   2.750   0.7776   0.01263   0.00335  -0.0911   0.5595   0.0836
   3.000   0.8028   0.01265   0.00346  -0.0905   0.5526   0.1268
   3.500   0.8937   0.01142   0.00391  -0.0988   0.5357   1.0000
   3.750   0.9178   0.01157   0.00407  -0.0980   0.5277   1.0000
   4.000   0.9415   0.01175   0.00422  -0.0972   0.5188   1.0000
   4.250   0.9653   0.01190   0.00440  -0.0964   0.5097   1.0000
   4.500   0.9887   0.01208   0.00460  -0.0955   0.4998   1.0000
   4.750   1.0118   0.01225   0.00479  -0.0945   0.4881   1.0000
   5.000   1.0349   0.01242   0.00501  -0.0936   0.4752   1.0000
   5.250   1.0572   0.01262   0.00522  -0.0925   0.4582   1.0000
   5.500   1.0788   0.01284   0.00546  -0.0913   0.4324   1.0000
   5.750   1.0964   0.01322   0.00568  -0.0894   0.3877   1.0000
   6.000   1.1119   0.01376   0.00602  -0.0872   0.3537   1.0000
   6.250   1.1288   0.01429   0.00646  -0.0853   0.3325   1.0000
   6.500   1.1462   0.01482   0.00696  -0.0835   0.3159   1.0000
   6.750   1.1618   0.01544   0.00749  -0.0815   0.2965   1.0000
   7.000   1.1787   0.01599   0.00801  -0.0797   0.2775   1.0000
   7.250   1.1954   0.01653   0.00853  -0.0779   0.2564   1.0000
   7.500   1.2109   0.01712   0.00906  -0.0760   0.2336   1.0000
   7.750   1.2249   0.01778   0.00964  -0.0738   0.1985   1.0000
   8.000   1.2261   0.01918   0.01055  -0.0699   0.1326   1.0000
   8.250   1.2338   0.02010   0.01139  -0.0668   0.1176   1.0000
   8.500   1.2427   0.02094   0.01224  -0.0639   0.1047   1.0000
   8.750   1.2544   0.02166   0.01301  -0.0615   0.0869   1.0000
   9.000   1.2560   0.02303   0.01408  -0.0580   0.0483   1.0000
   9.500   1.2611   0.02583   0.01680  -0.0517   0.0239   1.0000
   9.750   1.2670   0.02712   0.01816  -0.0493   0.0212   1.0000
  10.000   1.2744   0.02837   0.01955  -0.0471   0.0198   1.0000
  10.250   1.2805   0.02977   0.02108  -0.0450   0.0183   1.0000
  10.500   1.2853   0.03133   0.02276  -0.0430   0.0168   1.0000
  10.750   1.2880   0.03314   0.02468  -0.0410   0.0155   1.0000
  11.000   1.2876   0.03529   0.02696  -0.0390   0.0147   1.0000
  11.250   1.2843   0.03779   0.02960  -0.0371   0.0140   1.0000
  11.500   1.2845   0.04008   0.03201  -0.0356   0.0136   1.0000
  11.750   1.2864   0.04227   0.03434  -0.0342   0.0131   1.0000
  12.000   1.2882   0.04455   0.03674  -0.0331   0.0128   1.0000
  12.250   1.2899   0.04691   0.03923  -0.0320   0.0125   1.0000
  12.500   1.2919   0.04931   0.04174  -0.0311   0.0119   1.0000
  12.750   1.2939   0.05175   0.04436  -0.0304   0.0114   1.0000
  13.000   1.2963   0.05420   0.04691  -0.0299   0.0108   1.0000
  13.250   1.2970   0.05691   0.04973  -0.0293   0.0105   1.0000
  13.500   1.2971   0.05975   0.05267  -0.0289   0.0102   1.0000
  13.750   1.2967   0.06273   0.05575  -0.0285   0.0099   1.0000
  14.000   1.2960   0.06584   0.05896  -0.0279   0.0097   1.0000
  14.250   1.2954   0.06904   0.06227  -0.0274   0.0095   1.0000
  14.500   1.2959   0.07220   0.06560  -0.0273   0.0094   1.0000
  14.750   1.2950   0.07563   0.06921  -0.0274   0.0092   1.0000
  15.000   1.2929   0.07931   0.07308  -0.0277   0.0091   1.0000
  15.250   1.2885   0.08342   0.07741  -0.0283   0.0090   1.0000
  15.500   1.2835   0.08772   0.08190  -0.0292   0.0089   1.0000
  15.750   1.2759   0.09258   0.08698  -0.0305   0.0087   1.0000
  16.000   1.2674   0.09770   0.09230  -0.0322   0.0086   1.0000
  16.250   1.2574   0.10325   0.09806  -0.0342   0.0086   1.0000
  16.500   1.2469   0.10911   0.10411  -0.0368   0.0085   1.0000
  16.750   1.2352   0.11541   0.11061  -0.0397   0.0085   1.0000
  17.000   1.2227   0.12215   0.11755  -0.0432   0.0084   1.0000
  17.250   1.2109   0.12908   0.12466  -0.0471   0.0082   1.0000
  17.500   1.1981   0.13652   0.13227  -0.0515   0.0082   1.0000
  17.750   1.1829   0.14491   0.14085  -0.0565   0.0083   1.0000
  18.000   1.1683   0.15352   0.14963  -0.0619   0.0083   1.0000
  18.250   1.1502   0.16355   0.15982  -0.0681   0.0084   1.0000
  18.500   1.1320   0.17425   0.17066  -0.0748   0.0087   1.0000
  18.750   1.1135   0.18604   0.18255  -0.0819   0.0090   1.0000
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