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GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 490 AIRFOIL (goe490-il)
Reynolds number: 500,000
Max Cl/Cd: 89.64 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe490-il-500000-n5.txt
Download as CSV file: xf-goe490-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 490 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4117   0.10405   0.10174  -0.0271   1.0000   0.0083
 -10.250  -0.4171   0.09916   0.09688  -0.0284   1.0000   0.0087
  -9.750  -0.7026   0.02617   0.02272  -0.0696   0.9893   0.0081
  -9.500  -0.6771   0.02354   0.01974  -0.0713   0.9868   0.0084
  -9.250  -0.6528   0.02169   0.01763  -0.0719   0.9834   0.0089
  -9.000  -0.6274   0.02010   0.01576  -0.0724   0.9798   0.0093
  -8.750  -0.5992   0.01878   0.01419  -0.0733   0.9773   0.0098
  -8.500  -0.5726   0.01757   0.01281  -0.0737   0.9743   0.0107
  -8.250  -0.5464   0.01685   0.01199  -0.0737   0.9699   0.0116
  -8.000  -0.5168   0.01619   0.01122  -0.0743   0.9672   0.0128
  -7.500  -0.4606   0.01506   0.00990  -0.0748   0.9598   0.0153
  -7.250  -0.4306   0.01482   0.00962  -0.0752   0.9560   0.0168
  -7.000  -0.3994   0.01441   0.00911  -0.0760   0.9533   0.0185
  -6.750  -0.3706   0.01408   0.00868  -0.0762   0.9485   0.0197
  -6.500  -0.3413   0.01367   0.00824  -0.0766   0.9427   0.0213
  -6.250  -0.3056   0.01344   0.00795  -0.0782   0.9389   0.0230
  -6.000  -0.2733   0.01313   0.00756  -0.0792   0.9325   0.0248
  -5.750  -0.2383   0.01281   0.00714  -0.0807   0.9265   0.0263
  -5.500  -0.2027   0.01254   0.00677  -0.0823   0.9204   0.0273
  -5.250  -0.1696   0.01199   0.00611  -0.0835   0.9121   0.0284
  -5.000  -0.1374   0.01130   0.00531  -0.0845   0.9027   0.0303
  -4.750  -0.1048   0.01092   0.00484  -0.0854   0.8925   0.0317
  -4.500  -0.0752   0.01059   0.00442  -0.0857   0.8798   0.0328
  -4.250  -0.0468   0.01032   0.00405  -0.0857   0.8659   0.0341
  -4.000  -0.0194   0.01007   0.00369  -0.0855   0.8519   0.0352
  -3.750   0.0072   0.00984   0.00337  -0.0851   0.8385   0.0360
  -3.500   0.0336   0.00966   0.00309  -0.0846   0.8255   0.0367
  -3.250   0.0599   0.00949   0.00283  -0.0841   0.8123   0.0373
  -3.000   0.0859   0.00936   0.00261  -0.0835   0.7981   0.0378
  -2.750   0.1115   0.00922   0.00237  -0.0829   0.7832   0.0388
  -2.500   0.1371   0.00909   0.00215  -0.0822   0.7686   0.0407
  -2.250   0.1626   0.00899   0.00199  -0.0816   0.7545   0.0435
  -2.000   0.1879   0.00890   0.00185  -0.0809   0.7400   0.0486
  -1.750   0.2127   0.00875   0.00173  -0.0801   0.7257   0.0679
  -1.500   0.2375   0.00864   0.00167  -0.0794   0.7108   0.0980
  -1.250   0.2628   0.00862   0.00162  -0.0788   0.6966   0.1123
  -1.000   0.2881   0.00861   0.00158  -0.0781   0.6819   0.1248
  -0.750   0.3133   0.00862   0.00154  -0.0774   0.6658   0.1341
  -0.500   0.3379   0.00865   0.00151  -0.0766   0.6466   0.1437
  -0.250   0.3619   0.00869   0.00148  -0.0757   0.6228   0.1542
   0.000   0.3856   0.00877   0.00146  -0.0747   0.5968   0.1627
   0.500   0.4329   0.00886   0.00151  -0.0729   0.5444   0.2107
   0.750   0.4563   0.00895   0.00157  -0.0719   0.5159   0.2505
   1.000   0.4799   0.00907   0.00163  -0.0710   0.4894   0.2764
   1.250   0.5039   0.00918   0.00169  -0.0702   0.4676   0.2930
   1.500   0.5283   0.00927   0.00174  -0.0695   0.4520   0.3092
   1.750   0.5528   0.00934   0.00180  -0.0688   0.4373   0.3262
   2.000   0.5768   0.00937   0.00188  -0.0680   0.4229   0.3582
   3.000   0.7557   0.00876   0.00256  -0.0835   0.3681   1.0000
   3.250   0.7786   0.00891   0.00267  -0.0824   0.3575   1.0000
   3.500   0.8013   0.00907   0.00278  -0.0813   0.3451   1.0000
   3.750   0.8238   0.00925   0.00291  -0.0802   0.3311   1.0000
   4.000   0.8462   0.00944   0.00305  -0.0791   0.3156   1.0000
   4.250   0.8677   0.00968   0.00320  -0.0778   0.2944   1.0000
   4.500   0.8878   0.01002   0.00340  -0.0763   0.2664   1.0000
   4.750   0.9059   0.01051   0.00367  -0.0745   0.2293   1.0000
   5.000   0.9257   0.01088   0.00393  -0.0730   0.2048   1.0000
   5.250   0.9457   0.01125   0.00419  -0.0715   0.1841   1.0000
   5.500   0.9657   0.01163   0.00445  -0.0701   0.1618   1.0000
   5.750   0.9845   0.01209   0.00477  -0.0684   0.1364   1.0000
   6.000   1.0026   0.01260   0.00514  -0.0667   0.1125   1.0000
   6.250   1.0206   0.01312   0.00552  -0.0649   0.0873   1.0000
   6.500   1.0323   0.01410   0.00622  -0.0621   0.0357   1.0000
   6.750   1.0483   0.01477   0.00680  -0.0600   0.0158   1.0000
   7.000   1.0682   0.01514   0.00722  -0.0585   0.0131   1.0000
   7.250   1.0880   0.01550   0.00766  -0.0570   0.0122   1.0000
   7.500   1.1070   0.01592   0.00814  -0.0554   0.0112   1.0000
   7.750   1.1251   0.01639   0.00869  -0.0537   0.0102   1.0000
   8.000   1.1406   0.01705   0.00945  -0.0515   0.0091   1.0000
   8.250   1.1581   0.01753   0.00998  -0.0497   0.0088   1.0000
   8.500   1.1746   0.01806   0.01059  -0.0478   0.0083   1.0000
   8.750   1.1899   0.01864   0.01126  -0.0457   0.0079   1.0000
   9.000   1.2028   0.01924   0.01192  -0.0431   0.0074   1.0000
   9.250   1.2139   0.01991   0.01266  -0.0403   0.0072   1.0000
   9.500   1.2247   0.02062   0.01343  -0.0376   0.0069   1.0000
   9.750   1.2340   0.02142   0.01429  -0.0348   0.0065   1.0000
  10.000   1.2367   0.02263   0.01559  -0.0311   0.0062   1.0000
  10.250   1.2481   0.02336   0.01640  -0.0289   0.0060   1.0000
  10.500   1.2578   0.02421   0.01733  -0.0265   0.0057   1.0000
  10.750   1.2633   0.02536   0.01858  -0.0238   0.0056   1.0000
  11.000   1.2684   0.02659   0.01992  -0.0213   0.0054   1.0000
  11.250   1.2722   0.02798   0.02141  -0.0189   0.0053   1.0000
  11.500   1.2749   0.02953   0.02307  -0.0166   0.0052   1.0000
  11.750   1.2799   0.03100   0.02463  -0.0149   0.0050   1.0000
  12.000   1.2814   0.03285   0.02658  -0.0131   0.0049   1.0000
  12.250   1.2825   0.03486   0.02868  -0.0117   0.0048   1.0000
  12.500   1.2822   0.03714   0.03106  -0.0105   0.0047   1.0000
  12.750   1.2835   0.03939   0.03340  -0.0096   0.0046   1.0000
  13.000   1.2812   0.04215   0.03627  -0.0090   0.0046   1.0000
  13.250   1.2797   0.04494   0.03917  -0.0086   0.0045   1.0000
  13.500   1.2776   0.04794   0.04225  -0.0086   0.0044   1.0000
  13.750   1.2737   0.05126   0.04568  -0.0087   0.0044   1.0000
  14.000   1.2687   0.05482   0.04935  -0.0089   0.0043   1.0000
  14.250   1.2612   0.05879   0.05341  -0.0094   0.0042   1.0000
  14.500   1.2543   0.06280   0.05753  -0.0100   0.0042   1.0000
  14.750   1.2494   0.06669   0.06157  -0.0108   0.0041   1.0000
  15.000   1.2449   0.07069   0.06570  -0.0117   0.0041   1.0000
  15.250   1.2409   0.07485   0.07000  -0.0131   0.0040   1.0000
  15.500   1.2354   0.07915   0.07442  -0.0144   0.0040   1.0000
  15.750   1.2293   0.08369   0.07909  -0.0159   0.0039   1.0000
  16.000   1.2216   0.08839   0.08390  -0.0172   0.0040   1.0000
  16.250   1.2150   0.09323   0.08888  -0.0191   0.0039   1.0000
  16.500   1.2066   0.09851   0.09431  -0.0212   0.0038   1.0000
  16.750   1.1977   0.10393   0.09986  -0.0234   0.0037   1.0000
  17.000   1.1915   0.10916   0.10521  -0.0260   0.0036   1.0000
  17.250   1.1831   0.11459   0.11077  -0.0283   0.0036   1.0000
  17.500   1.1746   0.12043   0.11673  -0.0312   0.0035   1.0000
  17.750   1.1649   0.12649   0.12292  -0.0342   0.0035   1.0000
  18.000   1.1561   0.13258   0.12913  -0.0373   0.0035   1.0000
  18.250   1.1451   0.13922   0.13591  -0.0408   0.0035   1.0000
  18.500   1.1347   0.14598   0.14279  -0.0445   0.0034   1.0000
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