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GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 476 AIRFOIL (goe476-il)
Reynolds number: 200,000
Max Cl/Cd: 74.37 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe476-il-200000-n5.txt
Download as CSV file: xf-goe476-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 476 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1914   0.06840   0.06413  -0.1010   0.9152   0.0520
  -9.000  -0.3374   0.03259   0.02696  -0.1254   0.8567   0.0552
  -8.750  -0.3342   0.02944   0.02329  -0.1241   0.8440   0.0561
  -8.500  -0.3250   0.02712   0.02049  -0.1226   0.8321   0.0570
  -8.250  -0.3123   0.02538   0.01830  -0.1209   0.8209   0.0578
  -8.000  -0.2914   0.02437   0.01709  -0.1201   0.8109   0.0584
  -7.750  -0.2701   0.02376   0.01644  -0.1191   0.8004   0.0591
  -7.500  -0.2470   0.02318   0.01574  -0.1185   0.7913   0.0598
  -7.250  -0.2263   0.02255   0.01498  -0.1173   0.7816   0.0607
  -7.000  -0.2041   0.02184   0.01407  -0.1164   0.7729   0.0617
  -6.750  -0.1832   0.02111   0.01315  -0.1152   0.7638   0.0627
  -6.500  -0.1608   0.02040   0.01220  -0.1143   0.7553   0.0636
  -6.250  -0.1382   0.01977   0.01135  -0.1132   0.7472   0.0645
  -6.000  -0.1149   0.01923   0.01077  -0.1124   0.7388   0.0655
  -5.750  -0.0908   0.01885   0.01033  -0.1117   0.7310   0.0665
  -5.500  -0.0672   0.01848   0.00990  -0.1108   0.7223   0.0677
  -5.250  -0.0426   0.01809   0.00937  -0.1100   0.7148   0.0691
  -5.000  -0.0189   0.01768   0.00886  -0.1091   0.7066   0.0704
  -4.750   0.0058   0.01730   0.00832  -0.1084   0.6996   0.0717
  -4.500   0.0303   0.01691   0.00789  -0.1076   0.6933   0.0729
  -4.250   0.0547   0.01662   0.00759  -0.1069   0.6869   0.0744
  -4.000   0.0799   0.01637   0.00729  -0.1062   0.6811   0.0762
  -3.750   0.1053   0.01612   0.00695  -0.1056   0.6760   0.0783
  -3.500   0.1302   0.01587   0.00663  -0.1049   0.6700   0.0802
  -3.250   0.1548   0.01560   0.00637  -0.1041   0.6644   0.0821
  -3.000   0.1806   0.01541   0.00614  -0.1036   0.6596   0.0845
  -2.750   0.2056   0.01524   0.00594  -0.1029   0.6546   0.0875
  -2.500   0.2306   0.01505   0.00576  -0.1022   0.6495   0.0906
  -2.250   0.2560   0.01491   0.00562  -0.1015   0.6446   0.0944
  -1.750   0.3067   0.01467   0.00538  -0.1003   0.6350   0.1036
  -1.500   0.3319   0.01459   0.00529  -0.0995   0.6297   0.1102
  -1.250   0.3576   0.01453   0.00525  -0.0990   0.6251   0.1177
  -0.750   0.4089   0.01448   0.00518  -0.0978   0.6163   0.1351
  -0.500   0.4338   0.01443   0.00519  -0.0971   0.6115   0.1439
  -0.250   0.4595   0.01442   0.00515  -0.0965   0.6069   0.1528
   0.000   0.4856   0.01441   0.00512  -0.0960   0.6028   0.1614
   0.250   0.5100   0.01439   0.00513  -0.0952   0.5978   0.1694
   0.500   0.5341   0.01435   0.00516  -0.0944   0.5925   0.1782
   0.750   0.5591   0.01435   0.00514  -0.0937   0.5878   0.1872
   1.000   0.5848   0.01434   0.00514  -0.0931   0.5838   0.1975
   1.250   0.6085   0.01432   0.00520  -0.0922   0.5790   0.2085
   1.750   0.6560   0.01427   0.00529  -0.0904   0.5689   0.2431
   2.000   0.6804   0.01421   0.00530  -0.0896   0.5644   0.2743
   2.250   0.7008   0.01405   0.00541  -0.0881   0.5581   0.3322
   2.750   0.8817   0.01316   0.00598  -0.1143   0.5415   1.0000
   3.000   0.9030   0.01329   0.00608  -0.1130   0.5360   1.0000
   3.250   0.9247   0.01343   0.00616  -0.1116   0.5312   1.0000
   3.500   0.9457   0.01357   0.00627  -0.1102   0.5258   1.0000
   3.750   0.9658   0.01371   0.00641  -0.1086   0.5192   1.0000
   4.000   0.9864   0.01386   0.00650  -0.1070   0.5135   1.0000
   4.250   1.0069   0.01402   0.00664  -0.1055   0.5082   1.0000
   4.500   1.0268   0.01418   0.00681  -0.1039   0.5023   1.0000
   4.750   1.0464   0.01435   0.00694  -0.1022   0.4963   1.0000
   5.000   1.0657   0.01452   0.00710  -0.1005   0.4902   1.0000
   5.250   1.0842   0.01470   0.00728  -0.0986   0.4837   1.0000
   5.500   1.1030   0.01489   0.00743  -0.0968   0.4778   1.0000
   5.750   1.1205   0.01509   0.00764  -0.0947   0.4707   1.0000
   6.000   1.1374   0.01530   0.00782  -0.0925   0.4633   1.0000
   6.250   1.1542   0.01552   0.00802  -0.0904   0.4566   1.0000
   6.500   1.1700   0.01575   0.00827  -0.0881   0.4491   1.0000
   7.000   1.1983   0.01627   0.00876  -0.0828   0.4330   1.0000
   7.250   1.2084   0.01655   0.00899  -0.0794   0.4242   1.0000
   7.500   1.2186   0.01682   0.00929  -0.0761   0.4148   1.0000
   7.750   1.2280   0.01716   0.00958  -0.0727   0.4053   1.0000
   8.000   1.2380   0.01750   0.00995  -0.0696   0.3944   1.0000
   8.250   1.2478   0.01791   0.01035  -0.0665   0.3835   1.0000
   8.500   1.2560   0.01838   0.01079  -0.0633   0.3715   1.0000
   8.750   1.2649   0.01889   0.01131  -0.0603   0.3571   1.0000
   9.000   1.2715   0.01952   0.01191  -0.0571   0.3403   1.0000
   9.250   1.2750   0.02033   0.01264  -0.0537   0.3189   1.0000
   9.500   1.2743   0.02141   0.01361  -0.0499   0.2941   1.0000
   9.750   1.2715   0.02274   0.01482  -0.0463   0.2736   1.0000
  10.250   1.2724   0.02552   0.01746  -0.0405   0.2463   1.0000
  10.500   1.2752   0.02693   0.01885  -0.0382   0.2372   1.0000
  10.750   1.2787   0.02838   0.02029  -0.0361   0.2289   1.0000
  11.000   1.2828   0.02985   0.02176  -0.0342   0.2222   1.0000
  11.250   1.2886   0.03127   0.02319  -0.0326   0.2150   1.0000
  11.500   1.2918   0.03292   0.02483  -0.0309   0.2089   1.0000
  11.750   1.2996   0.03428   0.02624  -0.0296   0.2036   1.0000
  12.000   1.3063   0.03577   0.02775  -0.0283   0.1977   1.0000
  12.250   1.3103   0.03750   0.02949  -0.0269   0.1924   1.0000
  12.500   1.3183   0.03896   0.03101  -0.0259   0.1872   1.0000
  12.750   1.3256   0.04051   0.03261  -0.0249   0.1817   1.0000
  13.000   1.3303   0.04231   0.03442  -0.0238   0.1769   1.0000
  13.250   1.3376   0.04393   0.03611  -0.0230   0.1721   1.0000
  13.500   1.3445   0.04561   0.03785  -0.0222   0.1665   1.0000
  13.750   1.3475   0.04769   0.03994  -0.0214   0.1611   1.0000
  14.000   1.3546   0.04943   0.04176  -0.0207   0.1553   1.0000
  14.250   1.3581   0.05155   0.04391  -0.0200   0.1491   1.0000
  14.500   1.3620   0.05367   0.04608  -0.0195   0.1433   1.0000
  14.750   1.3651   0.05590   0.04834  -0.0189   0.1369   1.0000
  15.000   1.3665   0.05835   0.05082  -0.0185   0.1307   1.0000
  15.250   1.3684   0.06079   0.05329  -0.0181   0.1243   1.0000
  15.500   1.3689   0.06342   0.05595  -0.0177   0.1186   1.0000
  15.750   1.3691   0.06612   0.05869  -0.0175   0.1122   1.0000
  16.000   1.3686   0.06894   0.06154  -0.0173   0.1069   1.0000
  16.250   1.3683   0.07179   0.06443  -0.0172   0.1012   1.0000
  16.500   1.3664   0.07486   0.06753  -0.0172   0.0965   1.0000
  16.750   1.3662   0.07778   0.07051  -0.0172   0.0915   1.0000
  17.000   1.3627   0.08113   0.07387  -0.0174   0.0877   1.0000
  17.250   1.3635   0.08398   0.07679  -0.0175   0.0841   1.0000
  17.500   1.3613   0.08724   0.08010  -0.0178   0.0810   1.0000
  18.000   1.3584   0.09367   0.08664  -0.0185   0.0766   1.0000
  18.250   1.3578   0.09678   0.08982  -0.0189   0.0747   1.0000
  18.500   1.3566   0.10000   0.09310  -0.0195   0.0732   1.0000
  18.750   1.3548   0.10331   0.09646  -0.0201   0.0718   1.0000
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