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GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 100,000
Max Cl/Cd: 46.31 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe481a-il-100000-n5.txt
Download as CSV file: xf-goe481a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1587   0.09800   0.09243  -0.0660   0.9468   0.0776
  -7.250  -0.1620   0.09424   0.08869  -0.0677   0.9393   0.0767
  -6.750  -0.1957   0.08375   0.07818  -0.0743   0.9206   0.0747
  -6.500  -0.1912   0.08020   0.07462  -0.0761   0.9130   0.0744
  -6.250  -0.1871   0.07604   0.07043  -0.0785   0.9044   0.0741
  -6.000  -0.1873   0.07165   0.06599  -0.0802   0.8944   0.0739
  -5.750  -0.1798   0.06612   0.06035  -0.0840   0.8867   0.0737
  -5.500  -0.1857   0.06008   0.05412  -0.0855   0.8746   0.0741
  -5.250  -0.1811   0.05143   0.04502  -0.0899   0.8681   0.0751
  -5.000  -0.1723   0.04987   0.04342  -0.0879   0.8565   0.0757
  -4.750  -0.1532   0.04571   0.03898  -0.0892   0.8510   0.0762
  -4.500  -0.1463   0.04270   0.03571  -0.0874   0.8396   0.0767
  -4.250  -0.1262   0.03913   0.03178  -0.0877   0.8336   0.0776
  -4.000  -0.1139   0.03679   0.02913  -0.0858   0.8231   0.0788
  -3.750  -0.0944   0.03363   0.02543  -0.0851   0.8163   0.0809
  -3.500  -0.0768   0.03139   0.02274  -0.0835   0.8073   0.0826
  -3.250  -0.0516   0.03051   0.02180  -0.0828   0.7989   0.0835
  -3.000  -0.0239   0.02944   0.02062  -0.0825   0.7918   0.0847
  -2.750  -0.0018   0.02849   0.01951  -0.0813   0.7811   0.0862
  -2.500   0.0294   0.02712   0.01786  -0.0815   0.7747   0.0884
  -2.250   0.0522   0.02618   0.01671  -0.0802   0.7629   0.0906
  -2.000   0.0857   0.02557   0.01611  -0.0808   0.7551   0.0926
  -1.750   0.1139   0.02495   0.01539  -0.0804   0.7437   0.0951
  -1.500   0.1480   0.02391   0.01412  -0.0810   0.7345   0.0984
  -1.250   0.1819   0.02332   0.01350  -0.0817   0.7236   0.1009
  -1.000   0.2154   0.02281   0.01292  -0.0823   0.7122   0.1047
  -0.750   0.2555   0.02215   0.01212  -0.0840   0.7017   0.1101
  -0.500   0.2863   0.02185   0.01174  -0.0843   0.6888   0.1154
  -0.250   0.3250   0.02137   0.01115  -0.0859   0.6775   0.1217
   0.000   0.3574   0.02109   0.01073  -0.0864   0.6650   0.1301
   0.250   0.3899   0.02090   0.01048  -0.0870   0.6535   0.1384
   0.500   0.4248   0.02065   0.01015  -0.0881   0.6425   0.1474
   0.750   0.4522   0.02056   0.00996  -0.0878   0.6313   0.1562
   1.000   0.4865   0.02038   0.00971  -0.0888   0.6212   0.1658
   1.250   0.5101   0.02033   0.00968  -0.0879   0.6104   0.1737
   1.500   0.5428   0.02029   0.00951  -0.0886   0.6010   0.1849
   1.750   0.5658   0.02025   0.00957  -0.0876   0.5912   0.1941
   2.000   0.5951   0.02023   0.00949  -0.0878   0.5823   0.2042
   2.250   0.6202   0.02024   0.00952  -0.0871   0.5732   0.2121
   2.500   0.6458   0.02030   0.00953  -0.0865   0.5640   0.2196
   2.750   0.6767   0.02034   0.00955  -0.0870   0.5556   0.2277
   3.000   0.7008   0.02048   0.00970  -0.0863   0.5469   0.2367
   3.250   0.7340   0.02054   0.00973  -0.0872   0.5395   0.2488
   3.500   0.7554   0.02070   0.00994  -0.0860   0.5311   0.2637
   3.750   0.7811   0.02076   0.01011  -0.0856   0.5228   0.2982
   4.000   0.9057   0.02017   0.01100  -0.1062   0.5084   1.0000
   4.250   0.9273   0.02044   0.01112  -0.1049   0.5006   1.0000
   4.500   0.9450   0.02074   0.01134  -0.1028   0.4922   1.0000
   4.750   0.9617   0.02103   0.01155  -0.1005   0.4836   1.0000
   5.000   0.9810   0.02131   0.01171  -0.0988   0.4754   1.0000
   5.250   0.9946   0.02163   0.01202  -0.0960   0.4664   1.0000
   5.500   1.0151   0.02193   0.01218  -0.0945   0.4592   1.0000
   5.750   1.0294   0.02228   0.01254  -0.0920   0.4510   1.0000
   6.000   1.0456   0.02261   0.01281  -0.0898   0.4430   1.0000
   6.250   1.0627   0.02295   0.01309  -0.0878   0.4356   1.0000
   6.500   1.0768   0.02334   0.01348  -0.0853   0.4276   1.0000
   6.750   1.0953   0.02368   0.01374  -0.0836   0.4210   1.0000
   7.000   1.1103   0.02411   0.01419  -0.0813   0.4139   1.0000
   7.250   1.1254   0.02453   0.01460  -0.0791   0.4069   1.0000
   7.500   1.1443   0.02490   0.01488  -0.0776   0.4009   1.0000
   7.750   1.1564   0.02541   0.01546  -0.0750   0.3934   1.0000
   8.000   1.1711   0.02586   0.01591  -0.0728   0.3866   1.0000
   8.250   1.1876   0.02631   0.01629  -0.0709   0.3804   1.0000
   8.500   1.1997   0.02689   0.01695  -0.0685   0.3734   1.0000
   8.750   1.2140   0.02740   0.01744  -0.0664   0.3670   1.0000
   9.000   1.2290   0.02793   0.01795  -0.0645   0.3610   1.0000
   9.250   1.2399   0.02860   0.01870  -0.0620   0.3539   1.0000
   9.500   1.2533   0.02918   0.01926  -0.0599   0.3476   1.0000
   9.750   1.2658   0.02984   0.01993  -0.0578   0.3413   1.0000
  10.000   1.2749   0.03062   0.02079  -0.0553   0.3340   1.0000
  10.250   1.2872   0.03127   0.02138  -0.0532   0.3273   1.0000
  10.500   1.2943   0.03218   0.02239  -0.0506   0.3198   1.0000
  10.750   1.3017   0.03306   0.02329  -0.0481   0.3121   1.0000
  11.000   1.3099   0.03397   0.02419  -0.0457   0.3047   1.0000
  11.250   1.3147   0.03509   0.02539  -0.0432   0.2967   1.0000
  11.500   1.3226   0.03604   0.02628  -0.0410   0.2896   1.0000
  11.750   1.3242   0.03745   0.02783  -0.0384   0.2810   1.0000
  12.000   1.3296   0.03864   0.02900  -0.0363   0.2738   1.0000
  12.250   1.3321   0.04014   0.03058  -0.0341   0.2662   1.0000
  12.500   1.3346   0.04166   0.03213  -0.0320   0.2587   1.0000
  12.750   1.3366   0.04330   0.03380  -0.0301   0.2514   1.0000
  13.000   1.3371   0.04514   0.03572  -0.0282   0.2441   1.0000
  13.250   1.3398   0.04685   0.03740  -0.0266   0.2381   1.0000
  13.500   1.3396   0.04898   0.03965  -0.0251   0.2314   1.0000
  13.750   1.3408   0.05099   0.04168  -0.0238   0.2258   1.0000
  14.000   1.3427   0.05303   0.04374  -0.0226   0.2208   1.0000
  14.250   1.3421   0.05543   0.04625  -0.0216   0.2154   1.0000
  14.500   1.3425   0.05773   0.04858  -0.0206   0.2104   1.0000
  14.750   1.3449   0.05987   0.05072  -0.0198   0.2062   1.0000
  15.000   1.3423   0.06271   0.05370  -0.0192   0.2014   1.0000
  15.250   1.3416   0.06532   0.05636  -0.0186   0.1970   1.0000
  15.500   1.3453   0.06737   0.05837  -0.0180   0.1930   1.0000
  15.750   1.3414   0.07054   0.06166  -0.0178   0.1887   1.0000
  16.000   1.3372   0.07377   0.06501  -0.0176   0.1843   1.0000
  16.250   1.3385   0.07627   0.06753  -0.0173   0.1804   1.0000
  16.500   1.3430   0.07833   0.06956  -0.0170   0.1767   1.0000
  16.750   1.3330   0.08251   0.07392  -0.0174   0.1724   1.0000
  17.000   1.3287   0.08592   0.07742  -0.0176   0.1683   1.0000
  17.250   1.3338   0.08796   0.07944  -0.0174   0.1645   1.0000
  17.500   1.3328   0.09094   0.08249  -0.0176   0.1610   1.0000
  17.750   1.3190   0.09588   0.08762  -0.0186   0.1568   1.0000
  18.000   1.3150   0.09938   0.09118  -0.0192   0.1527   1.0000
  18.250   1.3263   0.10050   0.09223  -0.0189   0.1493   1.0000
  18.500   1.3088   0.10621   0.09815  -0.0205   0.1455   1.0000
  18.750   1.2917   0.11194   0.10405  -0.0223   0.1413   1.0000
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