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GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 479 AIRFOIL (goe479-il)
Reynolds number: 500,000
Max Cl/Cd: 101.1 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe479-il-500000.txt
Download as CSV file: xf-goe479-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 479 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3608   0.09400   0.09164  -0.0389   1.0000   0.0386
  -9.500  -0.3669   0.09128   0.08895  -0.0384   1.0000   0.0393
  -9.250  -0.4957   0.05594   0.05359  -0.0694   0.9924   0.0362
  -9.000  -0.4785   0.05175   0.04931  -0.0742   0.9876   0.0356
  -8.750  -0.5091   0.03359   0.03015  -0.0859   0.9757   0.0344
  -8.500  -0.4946   0.02712   0.02285  -0.0886   0.9715   0.0352
  -8.250  -0.4725   0.02505   0.02029  -0.0889   0.9664   0.0360
  -8.000  -0.4488   0.02229   0.01729  -0.0897   0.9622   0.0367
  -7.750  -0.4158   0.02123   0.01617  -0.0913   0.9600   0.0375
  -7.500  -0.3806   0.02022   0.01507  -0.0932   0.9584   0.0383
  -7.250  -0.3450   0.01924   0.01395  -0.0951   0.9567   0.0393
  -7.000  -0.3202   0.01829   0.01283  -0.0946   0.9502   0.0402
  -6.750  -0.2896   0.01729   0.01164  -0.0953   0.9459   0.0409
  -6.500  -0.2559   0.01654   0.01071  -0.0964   0.9426   0.0416
  -6.250  -0.2308   0.01516   0.00922  -0.0960   0.9354   0.0425
  -6.000  -0.2013   0.01444   0.00848  -0.0963   0.9283   0.0435
  -5.750  -0.1734   0.01394   0.00794  -0.0962   0.9196   0.0446
  -5.500  -0.1448   0.01339   0.00731  -0.0961   0.9104   0.0457
  -5.250  -0.1194   0.01289   0.00675  -0.0953   0.8989   0.0466
  -5.000  -0.0918   0.01247   0.00623  -0.0950   0.8887   0.0477
  -4.750  -0.0654   0.01200   0.00567  -0.0945   0.8775   0.0487
  -4.500  -0.0411   0.01138   0.00504  -0.0937   0.8647   0.0504
  -4.250  -0.0151   0.01108   0.00470  -0.0931   0.8515   0.0521
  -4.000   0.0110   0.01080   0.00435  -0.0925   0.8377   0.0538
  -3.750   0.0370   0.01057   0.00404  -0.0919   0.8235   0.0555
  -3.500   0.0617   0.01018   0.00358  -0.0911   0.8087   0.0579
  -3.000   0.1128   0.00983   0.00311  -0.0897   0.7791   0.0643
  -2.750   0.1377   0.00957   0.00282  -0.0890   0.7655   0.0692
  -2.500   0.1636   0.00945   0.00264  -0.0884   0.7534   0.0747
  -2.250   0.1891   0.00927   0.00245  -0.0877   0.7421   0.0844
  -2.000   0.2144   0.00909   0.00231  -0.0871   0.7308   0.1042
  -1.750   0.2396   0.00889   0.00223  -0.0865   0.7204   0.1462
  -1.500   0.2651   0.00876   0.00217  -0.0859   0.7110   0.1842
  -1.250   0.2908   0.00861   0.00214  -0.0854   0.7017   0.2242
  -1.000   0.3163   0.00849   0.00211  -0.0848   0.6931   0.2718
  -0.750   0.3412   0.00829   0.00209  -0.0842   0.6838   0.3343
  -0.500   0.3639   0.00792   0.00209  -0.0832   0.6756   0.4628
  -0.250   0.3836   0.00743   0.00215  -0.0815   0.6670   0.6359
   0.000   0.4018   0.00702   0.00221  -0.0791   0.6593   0.7966
   0.250   0.4760   0.00688   0.00236  -0.0885   0.6486   0.9619
   0.500   0.5335   0.00702   0.00241  -0.0946   0.6364   0.9907
   0.750   0.5832   0.00711   0.00239  -0.0992   0.6227   1.0000
   1.000   0.6056   0.00719   0.00238  -0.0980   0.6116   1.0000
   1.250   0.6287   0.00725   0.00240  -0.0969   0.6012   1.0000
   1.500   0.6515   0.00735   0.00243  -0.0958   0.5912   1.0000
   1.750   0.6745   0.00743   0.00246  -0.0947   0.5798   1.0000
   2.000   0.6976   0.00752   0.00250  -0.0936   0.5682   1.0000
   2.250   0.7204   0.00764   0.00255  -0.0925   0.5571   1.0000
   2.500   0.7431   0.00776   0.00261  -0.0913   0.5445   1.0000
   2.750   0.7660   0.00787   0.00268  -0.0902   0.5311   1.0000
   3.000   0.7888   0.00800   0.00276  -0.0890   0.5177   1.0000
   3.250   0.8110   0.00816   0.00285  -0.0878   0.5024   1.0000
   3.500   0.8330   0.00833   0.00295  -0.0865   0.4863   1.0000
   3.750   0.8550   0.00852   0.00306  -0.0852   0.4716   1.0000
   4.000   0.8770   0.00872   0.00319  -0.0840   0.4579   1.0000
   4.250   0.8989   0.00894   0.00334  -0.0827   0.4443   1.0000
   4.500   0.9207   0.00915   0.00350  -0.0815   0.4311   1.0000
   4.750   0.9433   0.00934   0.00365  -0.0804   0.4185   1.0000
   5.000   0.9655   0.00955   0.00383  -0.0792   0.4062   1.0000
   5.250   0.9874   0.00977   0.00400  -0.0780   0.3934   1.0000
   5.500   1.0090   0.01000   0.00419  -0.0768   0.3797   1.0000
   5.750   1.0304   0.01024   0.00439  -0.0755   0.3632   1.0000
   6.000   1.0516   0.01049   0.00458  -0.0742   0.3448   1.0000
   6.250   1.0720   0.01078   0.00481  -0.0728   0.3241   1.0000
   6.500   1.0909   0.01116   0.00507  -0.0711   0.3001   1.0000
   6.750   1.1086   0.01160   0.00538  -0.0693   0.2729   1.0000
   7.000   1.1258   0.01208   0.00574  -0.0674   0.2473   1.0000
   7.250   1.1421   0.01261   0.00613  -0.0654   0.2239   1.0000
   7.500   1.1571   0.01320   0.00658  -0.0632   0.1965   1.0000
   7.750   1.1677   0.01402   0.00714  -0.0603   0.1530   1.0000
   8.000   1.1621   0.01551   0.00811  -0.0548   0.0772   1.0000
   8.250   1.1675   0.01643   0.00889  -0.0511   0.0582   1.0000
   8.500   1.1805   0.01701   0.00948  -0.0486   0.0542   1.0000
   8.750   1.1920   0.01768   0.01017  -0.0460   0.0511   1.0000
   9.000   1.2045   0.01832   0.01084  -0.0436   0.0492   1.0000
   9.250   1.2181   0.01891   0.01149  -0.0415   0.0478   1.0000
   9.500   1.2306   0.01957   0.01220  -0.0394   0.0464   1.0000
   9.750   1.2413   0.02036   0.01303  -0.0371   0.0451   1.0000
  10.000   1.2498   0.02129   0.01400  -0.0346   0.0440   1.0000
  10.250   1.2547   0.02247   0.01523  -0.0318   0.0429   1.0000
  10.500   1.2609   0.02363   0.01646  -0.0294   0.0422   1.0000
  10.750   1.2716   0.02456   0.01746  -0.0277   0.0416   1.0000
  11.000   1.2808   0.02562   0.01860  -0.0259   0.0410   1.0000
  11.250   1.2891   0.02681   0.01985  -0.0241   0.0402   1.0000
  11.500   1.2969   0.02808   0.02118  -0.0225   0.0394   1.0000
  11.750   1.3031   0.02952   0.02269  -0.0210   0.0388   1.0000
  12.000   1.3089   0.03108   0.02430  -0.0195   0.0382   1.0000
  12.250   1.3134   0.03280   0.02608  -0.0182   0.0376   1.0000
  12.500   1.3146   0.03489   0.02821  -0.0169   0.0369   1.0000
  12.750   1.3133   0.03725   0.03063  -0.0154   0.0363   1.0000
  13.000   1.3170   0.03924   0.03268  -0.0144   0.0358   1.0000
  13.250   1.3242   0.04096   0.03449  -0.0137   0.0354   1.0000
  13.500   1.3308   0.04277   0.03639  -0.0130   0.0349   1.0000
  13.750   1.3366   0.04469   0.03838  -0.0124   0.0344   1.0000
  14.000   1.3421   0.04667   0.04044  -0.0119   0.0338   1.0000
  14.250   1.3472   0.04874   0.04258  -0.0115   0.0331   1.0000
  14.500   1.3521   0.05086   0.04476  -0.0111   0.0326   1.0000
  14.750   1.3562   0.05307   0.04702  -0.0108   0.0321   1.0000
  15.000   1.3606   0.05527   0.04926  -0.0105   0.0316   1.0000
  15.250   1.3651   0.05740   0.05141  -0.0099   0.0311   1.0000
  15.500   1.3709   0.05929   0.05332  -0.0088   0.0303   1.0000
  15.750   1.3737   0.06187   0.05603  -0.0090   0.0300   1.0000
  16.000   1.3757   0.06461   0.05888  -0.0094   0.0295   1.0000
  16.250   1.3788   0.06719   0.06157  -0.0095   0.0290   1.0000
  16.500   1.3812   0.06989   0.06436  -0.0098   0.0286   1.0000
  16.750   1.3835   0.07265   0.06721  -0.0102   0.0281   1.0000
  17.000   1.3850   0.07557   0.07021  -0.0107   0.0277   1.0000
  17.250   1.3860   0.07860   0.07332  -0.0113   0.0272   1.0000
  17.500   1.3875   0.08160   0.07638  -0.0121   0.0268   1.0000
  17.750   1.3904   0.08431   0.07912  -0.0126   0.0264   1.0000
  18.000   1.3978   0.08602   0.08083  -0.0116   0.0256   1.0000
  18.250   1.3934   0.09009   0.08506  -0.0131   0.0254   1.0000
  18.500   1.3870   0.09463   0.08976  -0.0151   0.0251   1.0000
  18.750   1.3823   0.09891   0.09418  -0.0168   0.0247   1.0000
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