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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 50,000
Max Cl/Cd: 42.81 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe483-il-50000.txt
Download as CSV file: xf-goe483-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3167   0.11303   0.10632  -0.0216   1.0000   0.1027
  -8.250  -0.3205   0.11309   0.10651  -0.0232   1.0000   0.1041
  -8.000  -0.3292   0.11394   0.10752  -0.0247   1.0000   0.1046
  -7.750  -0.3020   0.10434   0.09781  -0.0224   1.0000   0.1104
  -7.500  -0.3004   0.10234   0.09590  -0.0224   1.0000   0.1146
  -7.250  -0.3054   0.10180   0.09551  -0.0230   1.0000   0.1172
  -7.000  -0.3098   0.10250   0.09635  -0.0264   1.0000   0.1184
  -6.750  -0.2993   0.09618   0.09009  -0.0230   1.0000   0.1213
  -6.500  -0.2947   0.09322   0.08720  -0.0220   1.0000   0.1254
  -6.250  -0.2941   0.09160   0.08568  -0.0226   1.0000   0.1295
  -6.000  -0.2952   0.09207   0.08625  -0.0266   1.0000   0.1321
  -5.750  -0.2931   0.08804   0.08232  -0.0242   1.0000   0.1341
  -5.500  -0.2910   0.08483   0.07918  -0.0215   1.0000   0.1383
  -5.250  -0.2889   0.08324   0.07764  -0.0221   1.0000   0.1435
  -5.000  -0.2824   0.08225   0.07667  -0.0260   1.0000   0.1469
  -4.750  -0.2822   0.07839   0.07290  -0.0220   1.0000   0.1507
  -4.500  -0.2729   0.07670   0.07120  -0.0241   1.0000   0.1583
  -4.250  -0.2648   0.07380   0.06834  -0.0249   1.0000   0.1623
  -4.000  -0.2570   0.07110   0.06566  -0.0244   1.0000   0.1696
  -3.750  -0.2418   0.06855   0.06303  -0.0271   1.0000   0.1764
  -3.250  -0.2042   0.06399   0.05835  -0.0327   1.0000   0.2018
  -3.000  -0.1885   0.06119   0.05553  -0.0337   1.0000   0.2154
  -2.750  -0.1724   0.05820   0.05252  -0.0346   1.0000   0.2295
  -2.500  -0.1547   0.05527   0.04956  -0.0356   1.0000   0.2438
  -2.250  -0.1373   0.05236   0.04664  -0.0362   1.0000   0.2605
  -2.000  -0.1142   0.04982   0.04402  -0.0384   1.0000   0.2856
  -1.750  -0.0948   0.04709   0.04127  -0.0392   1.0000   0.3153
  -1.500  -0.0808   0.04430   0.03847  -0.0386   1.0000   0.3694
  -1.250  -0.0735   0.04124   0.03553  -0.0358   1.0000   0.4404
  -1.000  -0.0518   0.03879   0.03302  -0.0366   1.0000   0.4905
  -0.750  -0.0238   0.03643   0.03059  -0.0387   1.0000   0.5102
  -0.500   0.0271   0.03539   0.02912  -0.0467   1.0000   0.4891
  -0.250   0.1678   0.03496   0.02648  -0.0689   0.9873   0.1831
   0.000   0.2254   0.03351   0.02440  -0.0748   0.9742   0.1996
   0.250   0.2802   0.03219   0.02249  -0.0798   0.9606   0.2152
   0.500   0.3305   0.03133   0.02136  -0.0844   0.9459   0.2602
   0.750   0.3836   0.03051   0.02016  -0.0892   0.9312   0.3191
   1.000   0.4341   0.02977   0.01931  -0.0934   0.9165   0.3797
   1.250   0.4814   0.02899   0.01884  -0.0971   0.9016   0.4535
   1.500   0.5299   0.02801   0.01866  -0.1005   0.8862   1.0000
   1.750   0.5681   0.02862   0.01887  -0.1023   0.8685   1.0000
   2.000   0.6057   0.02917   0.01916  -0.1041   0.8513   1.0000
   2.250   0.6462   0.02960   0.01941  -0.1061   0.8349   1.0000
   2.500   0.6868   0.02993   0.01963  -0.1079   0.8192   1.0000
   2.750   0.7251   0.03018   0.01986  -0.1090   0.8037   1.0000
   3.000   0.7617   0.03039   0.02004  -0.1097   0.7885   1.0000
   3.250   0.7881   0.03094   0.02059  -0.1092   0.7712   1.0000
   3.500   0.8151   0.03144   0.02112  -0.1086   0.7542   1.0000
   3.750   0.8446   0.03177   0.02156  -0.1082   0.7381   1.0000
   4.000   0.8744   0.03202   0.02187  -0.1076   0.7223   1.0000
   4.250   0.9047   0.03217   0.02211  -0.1068   0.7068   1.0000
   4.500   0.9350   0.03224   0.02228  -0.1059   0.6916   1.0000
   4.750   0.9604   0.03264   0.02279  -0.1047   0.6751   1.0000
   5.000   0.9817   0.03333   0.02369  -0.1033   0.6572   1.0000
   5.250   1.0080   0.03362   0.02413  -0.1020   0.6408   1.0000
   5.500   1.0362   0.03372   0.02440  -0.1007   0.6247   1.0000
   5.750   1.0653   0.03375   0.02460  -0.0994   0.6090   1.0000
   6.000   1.0902   0.03421   0.02533  -0.0979   0.5923   1.0000
   6.250   1.1101   0.03522   0.02657  -0.0964   0.5745   1.0000
   6.500   1.1347   0.03580   0.02739  -0.0950   0.5575   1.0000
   6.750   1.1660   0.03504   0.02682  -0.0926   0.5358   1.0000
   7.000   1.1965   0.03185   0.02357  -0.0876   0.4914   1.0000
   7.250   1.2162   0.03004   0.02184  -0.0831   0.4475   1.0000
   7.500   1.2267   0.02871   0.02054  -0.0781   0.3966   1.0000
   7.750   1.2248   0.02861   0.02030  -0.0725   0.3188   1.0000
   8.000   1.2147   0.03087   0.02161  -0.0675   0.1819   1.0000
   8.250   1.2081   0.03440   0.02429  -0.0641   0.1196   1.0000
   8.500   1.2069   0.03733   0.02693  -0.0612   0.1015   1.0000
   8.750   1.2096   0.03973   0.02936  -0.0582   0.0922   1.0000
   9.000   1.2151   0.04219   0.03184  -0.0555   0.0862   1.0000
   9.250   1.2333   0.04450   0.03427  -0.0534   0.0805   1.0000
   9.500   1.2727   0.04755   0.03734  -0.0532   0.0739   1.0000
   9.750   1.3023   0.05064   0.04079  -0.0525   0.0688   1.0000
  10.000   1.3335   0.05471   0.04519  -0.0522   0.0674   1.0000
  10.250   1.3506   0.05902   0.04999  -0.0508   0.0676   1.0000
  10.500   1.3536   0.06332   0.05486  -0.0487   0.0685   1.0000
  10.750   1.3490   0.06773   0.05977  -0.0464   0.0695   1.0000
  11.000   1.3375   0.07198   0.06442  -0.0440   0.0705   1.0000
  11.250   1.3209   0.07614   0.06891  -0.0419   0.0713   1.0000
  11.500   1.3017   0.08058   0.07362  -0.0407   0.0720   1.0000
  11.750   1.2807   0.08550   0.07878  -0.0406   0.0727   1.0000
  12.000   1.2584   0.09099   0.08447  -0.0417   0.0733   1.0000
  12.250   1.2357   0.09709   0.09074  -0.0439   0.0740   1.0000
  12.500   1.2130   0.10392   0.09772  -0.0471   0.0746   1.0000
  12.750   1.1928   0.11130   0.10519  -0.0509   0.0754   1.0000
  13.000   1.1840   0.11828   0.11222  -0.0535   0.0764   1.0000
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