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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.78 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe408-il-1000000.txt
Download as CSV file: xf-goe408-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3344   0.08990   0.08843  -0.0200   1.0000   0.0136
  -8.750  -0.3337   0.08679   0.08533  -0.0199   1.0000   0.0137
  -8.500  -0.3271   0.08531   0.08386  -0.0192   1.0000   0.0142
  -8.250  -0.3275   0.08235   0.08092  -0.0191   1.0000   0.0144
  -8.000  -0.3300   0.07916   0.07774  -0.0190   1.0000   0.0145
  -7.250  -0.5450   0.01793   0.01417  -0.0457   0.9796   0.0124
  -7.000  -0.5206   0.01593   0.01185  -0.0455   0.9775   0.0130
  -6.750  -0.4912   0.01475   0.01044  -0.0460   0.9760   0.0133
  -6.500  -0.4614   0.01349   0.00896  -0.0466   0.9749   0.0149
  -6.250  -0.4346   0.01296   0.00837  -0.0463   0.9717   0.0164
  -6.000  -0.4076   0.01228   0.00755  -0.0461   0.9678   0.0172
  -5.750  -0.3739   0.01187   0.00714  -0.0473   0.9653   0.0196
  -5.500  -0.3359   0.01171   0.00697  -0.0494   0.9635   0.0219
  -5.250  -0.3120   0.01151   0.00680  -0.0482   0.9562   0.0237
  -5.000  -0.2758   0.01218   0.00762  -0.0498   0.9522   0.0252
  -4.750  -0.2524   0.01221   0.00766  -0.0485   0.9432   0.0265
  -4.500  -0.2256   0.01218   0.00760  -0.0481   0.9339   0.0277
  -4.250  -0.1972   0.01189   0.00727  -0.0480   0.9250   0.0292
  -4.000  -0.1616   0.01221   0.00766  -0.0496   0.9160   0.0301
  -3.750  -0.1149   0.01227   0.00773  -0.0536   0.9079   0.0313
  -3.500  -0.0627   0.01207   0.00746  -0.0590   0.8983   0.0335
  -3.250   0.0000   0.01249   0.00781  -0.0668   0.8839   0.0351
  -3.000   0.0519   0.01094   0.00599  -0.0727   0.8620   0.0376
  -2.750   0.0941   0.01088   0.00578  -0.0760   0.8289   0.0389
  -2.500   0.1223   0.01073   0.00544  -0.0761   0.7967   0.0401
  -2.250   0.1460   0.01038   0.00492  -0.0750   0.7716   0.0410
  -2.000   0.1694   0.01012   0.00450  -0.0739   0.7511   0.0420
  -1.750   0.1934   0.01005   0.00433  -0.0729   0.7349   0.0431
  -1.500   0.2174   0.00988   0.00405  -0.0719   0.7201   0.0437
  -1.250   0.2418   0.00978   0.00387  -0.0710   0.7073   0.0441
  -1.000   0.2659   0.00979   0.00381  -0.0700   0.6943   0.0445
  -0.750   0.2904   0.00915   0.00308  -0.0693   0.6837   0.0450
  -0.500   0.3138   0.00866   0.00253  -0.0682   0.6729   0.0457
  -0.250   0.3364   0.00833   0.00217  -0.0670   0.6622   0.0468
   0.000   0.3590   0.00820   0.00201  -0.0657   0.6496   0.0482
   0.250   0.3821   0.00811   0.00189  -0.0645   0.6382   0.0496
   0.500   0.4047   0.00805   0.00177  -0.0633   0.6252   0.0507
   0.750   0.4270   0.00800   0.00167  -0.0619   0.6086   0.0518
   1.000   0.4500   0.00796   0.00158  -0.0608   0.5952   0.0527
   1.250   0.4731   0.00794   0.00151  -0.0596   0.5796   0.0537
   1.500   0.4961   0.00795   0.00146  -0.0585   0.5618   0.0543
   1.750   0.5190   0.00798   0.00142  -0.0573   0.5410   0.0552
   2.000   0.5421   0.00805   0.00141  -0.0562   0.5210   0.0558
   2.250   0.5657   0.00805   0.00135  -0.0552   0.5033   0.0591
   2.500   0.5897   0.00810   0.00135  -0.0543   0.4873   0.0632
   2.750   0.6137   0.00817   0.00139  -0.0534   0.4721   0.0662
   3.000   0.6377   0.00825   0.00144  -0.0526   0.4581   0.0732
   3.250   0.6616   0.00824   0.00155  -0.0517   0.4444   0.1434
   3.500   0.9212   0.00778   0.00269  -0.1073   0.3821   1.0000
   3.750   0.9450   0.00794   0.00280  -0.1064   0.3688   1.0000
   4.000   0.9685   0.00810   0.00292  -0.1055   0.3541   1.0000
   4.250   0.9918   0.00828   0.00304  -0.1045   0.3376   1.0000
   4.500   1.0141   0.00853   0.00319  -0.1034   0.3139   1.0000
   4.750   1.0354   0.00885   0.00338  -0.1021   0.2820   1.0000
   5.000   1.0562   0.00921   0.00359  -0.1007   0.2493   1.0000
   5.250   1.0740   0.00977   0.00389  -0.0987   0.2010   1.0000
   5.500   1.0936   0.01019   0.00417  -0.0971   0.1727   1.0000
   5.750   1.1144   0.01052   0.00442  -0.0957   0.1557   1.0000
   6.000   1.1355   0.01083   0.00468  -0.0944   0.1422   1.0000
   6.250   1.1562   0.01115   0.00495  -0.0930   0.1275   1.0000
   6.500   1.1771   0.01146   0.00521  -0.0916   0.1162   1.0000
   6.750   1.1973   0.01181   0.00550  -0.0901   0.1008   1.0000
   7.250   1.2292   0.01307   0.00647  -0.0856   0.0467   1.0000
   7.500   1.2487   0.01344   0.00685  -0.0840   0.0395   1.0000
   7.750   1.2659   0.01395   0.00731  -0.0819   0.0284   1.0000
   8.000   1.2815   0.01458   0.00785  -0.0796   0.0190   1.0000
   8.250   1.2999   0.01499   0.00832  -0.0778   0.0170   1.0000
   8.500   1.3160   0.01555   0.00888  -0.0755   0.0146   1.0000
   8.750   1.3314   0.01614   0.00953  -0.0731   0.0132   1.0000
   9.000   1.3484   0.01658   0.01003  -0.0711   0.0124   1.0000
   9.250   1.3644   0.01706   0.01057  -0.0689   0.0119   1.0000
   9.500   1.3788   0.01761   0.01117  -0.0664   0.0110   1.0000
   9.750   1.3878   0.01830   0.01192  -0.0629   0.0104   1.0000
  10.000   1.3899   0.01920   0.01293  -0.0580   0.0098   1.0000
  10.250   1.3992   0.01977   0.01358  -0.0546   0.0095   1.0000
  10.500   1.4094   0.02033   0.01420  -0.0515   0.0092   1.0000
  10.750   1.4184   0.02098   0.01494  -0.0482   0.0089   1.0000
  11.000   1.4270   0.02167   0.01570  -0.0450   0.0085   1.0000
  11.250   1.4375   0.02230   0.01639  -0.0422   0.0082   1.0000
  11.500   1.4454   0.02308   0.01723  -0.0392   0.0079   1.0000
  11.750   1.4497   0.02409   0.01833  -0.0356   0.0078   1.0000
  12.000   1.4557   0.02504   0.01934  -0.0326   0.0074   1.0000
  12.250   1.4524   0.02661   0.02101  -0.0285   0.0071   1.0000
  12.500   1.4332   0.02944   0.02403  -0.0231   0.0068   1.0000
  12.750   1.4343   0.03106   0.02576  -0.0206   0.0068   1.0000
  13.000   1.4412   0.03231   0.02708  -0.0189   0.0067   1.0000
  13.250   1.4430   0.03410   0.02897  -0.0171   0.0066   1.0000
  13.500   1.4417   0.03632   0.03132  -0.0153   0.0065   1.0000
  13.750   1.4472   0.03801   0.03308  -0.0144   0.0064   1.0000
  14.000   1.4415   0.04098   0.03620  -0.0132   0.0063   1.0000
  14.250   1.4424   0.04338   0.03870  -0.0126   0.0061   1.0000
  14.500   1.4326   0.04710   0.04256  -0.0119   0.0063   1.0000
  14.750   1.4342   0.04967   0.04522  -0.0119   0.0060   1.0000
  15.000   1.4293   0.05306   0.04873  -0.0120   0.0059   1.0000
  15.250   1.4213   0.05699   0.05279  -0.0122   0.0058   1.0000
  15.500   1.4091   0.06156   0.05750  -0.0126   0.0059   1.0000
  15.750   1.4083   0.06486   0.06088  -0.0135   0.0056   1.0000
  16.000   1.4013   0.06906   0.06519  -0.0145   0.0056   1.0000
  16.250   1.3847   0.07471   0.07099  -0.0158   0.0057   1.0000
  16.500   1.3826   0.07852   0.07487  -0.0172   0.0055   1.0000
  16.750   1.3615   0.08514   0.08167  -0.0190   0.0057   1.0000
  17.000   1.3567   0.08965   0.08626  -0.0209   0.0055   1.0000
  17.250   1.3522   0.09423   0.09089  -0.0229   0.0052   1.0000
  17.500   1.3323   0.10112   0.09794  -0.0253   0.0053   1.0000
  17.750   1.3170   0.10752   0.10448  -0.0278   0.0054   1.0000
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