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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 50,000
Max Cl/Cd: 38.93 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe178-il-50000-n5.txt
Download as CSV file: xf-goe178-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3506   0.10057   0.09405  -0.0195   1.0000   0.1054
  -7.500  -0.3555   0.09894   0.09256  -0.0234   1.0000   0.1083
  -7.250  -0.3549   0.09675   0.09045  -0.0302   1.0000   0.1092
  -7.000  -0.3395   0.09152   0.08521  -0.0232   1.0000   0.1147
  -6.750  -0.3342   0.08867   0.08242  -0.0251   1.0000   0.1195
  -6.500  -0.3321   0.08658   0.08040  -0.0342   1.0000   0.1236
  -6.250  -0.3245   0.08268   0.07657  -0.0350   1.0000   0.1245
  -5.750  -0.2963   0.07119   0.06491  -0.0433   1.0000   0.0789
  -5.500  -0.2848   0.06749   0.06118  -0.0449   1.0000   0.0787
  -5.250  -0.2708   0.06365   0.05727  -0.0474   1.0000   0.0787
  -5.000  -0.2580   0.06018   0.05377  -0.0483   1.0000   0.0778
  -4.750  -0.2434   0.05668   0.05021  -0.0496   1.0000   0.0760
  -4.500  -0.2253   0.05294   0.04633  -0.0518   1.0000   0.0744
  -4.250  -0.2045   0.04916   0.04234  -0.0544   1.0000   0.0732
  -4.000  -0.1581   0.04443   0.03713  -0.0620   0.9909   0.0755
  -3.750  -0.1085   0.03991   0.03201  -0.0691   0.9801   0.0770
  -3.500  -0.0608   0.03605   0.02757  -0.0749   0.9687   0.0767
  -3.250  -0.0141   0.03283   0.02373  -0.0797   0.9564   0.0772
  -3.000   0.0314   0.03017   0.02043  -0.0837   0.9432   0.0783
  -2.750   0.0735   0.02812   0.01794  -0.0867   0.9277   0.0811
  -2.500   0.1114   0.02686   0.01654  -0.0888   0.9093   0.0871
  -2.250   0.1503   0.02539   0.01463  -0.0905   0.8905   0.0919
  -2.000   0.1857   0.02407   0.01300  -0.0914   0.8690   0.0957
  -1.750   0.2214   0.02297   0.01176  -0.0922   0.8490   0.1020
  -1.500   0.2553   0.02202   0.01054  -0.0926   0.8265   0.1120
  -1.250   0.2882   0.02120   0.00960  -0.0928   0.8051   0.1294
  -1.000   0.3177   0.02072   0.00909  -0.0927   0.7812   0.1629
  -0.500   0.3738   0.01967   0.00835  -0.0923   0.7374   0.2807
  -0.250   0.3947   0.01751   0.00804  -0.0899   0.7186   1.0000
   0.000   0.4227   0.01774   0.00772  -0.0894   0.7009   1.0000
   0.250   0.4503   0.01799   0.00756  -0.0889   0.6848   1.0000
   0.500   0.4776   0.01826   0.00750  -0.0885   0.6699   1.0000
   0.750   0.5049   0.01856   0.00751  -0.0882   0.6561   1.0000
   1.000   0.5321   0.01888   0.00760  -0.0880   0.6433   1.0000
   1.250   0.5594   0.01922   0.00773  -0.0878   0.6317   1.0000
   1.500   0.5867   0.01957   0.00790  -0.0876   0.6214   1.0000
   1.750   0.6141   0.01992   0.00809  -0.0874   0.6117   1.0000
   2.000   0.6415   0.02032   0.00839  -0.0874   0.6015   1.0000
   2.250   0.6691   0.02071   0.00867  -0.0873   0.5928   1.0000
   2.500   0.6962   0.02112   0.00901  -0.0872   0.5835   1.0000
   2.750   0.7231   0.02156   0.00940  -0.0870   0.5743   1.0000
   3.000   0.7502   0.02194   0.00971  -0.0867   0.5657   1.0000
   3.250   0.7762   0.02240   0.01018  -0.0865   0.5550   1.0000
   3.500   0.8024   0.02285   0.01061  -0.0862   0.5452   1.0000
   3.750   0.8290   0.02326   0.01099  -0.0859   0.5363   1.0000
   4.000   0.8545   0.02378   0.01160  -0.0856   0.5264   1.0000
   4.250   0.8807   0.02426   0.01209  -0.0853   0.5182   1.0000
   4.500   0.9064   0.02481   0.01272  -0.0850   0.5094   1.0000
   4.750   0.9320   0.02538   0.01341  -0.0847   0.5013   1.0000
   5.000   0.9577   0.02594   0.01405  -0.0844   0.4932   1.0000
   5.250   0.9825   0.02660   0.01487  -0.0841   0.4848   1.0000
   5.500   1.0083   0.02717   0.01556  -0.0837   0.4773   1.0000
   5.750   1.0322   0.02793   0.01654  -0.0834   0.4684   1.0000
   6.000   1.0582   0.02850   0.01720  -0.0829   0.4613   1.0000
   6.250   1.0808   0.02942   0.01840  -0.0825   0.4523   1.0000
   6.500   1.1065   0.02997   0.01910  -0.0820   0.4449   1.0000
   6.750   1.1284   0.03077   0.02018  -0.0813   0.4341   1.0000
   7.000   1.1506   0.03146   0.02110  -0.0805   0.4233   1.0000
   7.250   1.1743   0.03189   0.02171  -0.0797   0.4128   1.0000
   7.500   1.1974   0.03211   0.02215  -0.0785   0.4003   1.0000
   7.750   1.2147   0.03233   0.02267  -0.0769   0.3807   1.0000
   8.000   1.2325   0.03227   0.02285  -0.0751   0.3595   1.0000
   8.250   1.2464   0.03202   0.02278  -0.0728   0.3275   1.0000
   8.500   1.2572   0.03234   0.02323  -0.0704   0.2809   1.0000
   8.750   1.2592   0.03368   0.02408  -0.0674   0.2017   1.0000
   9.000   1.2408   0.03772   0.02705  -0.0642   0.0913   1.0000
   9.250   1.2269   0.04140   0.03053  -0.0614   0.0741   1.0000
   9.500   1.2132   0.04516   0.03428  -0.0594   0.0672   1.0000
   9.750   1.2024   0.04906   0.03831  -0.0586   0.0621   1.0000
  10.000   1.1914   0.05341   0.04284  -0.0587   0.0585   1.0000
  10.250   1.1799   0.05817   0.04774  -0.0594   0.0561   1.0000
  10.500   1.1682   0.06314   0.05281  -0.0603   0.0543   1.0000
  10.750   1.1610   0.06755   0.05741  -0.0609   0.0522   1.0000
  11.000   1.1567   0.07154   0.06158  -0.0612   0.0500   1.0000
  11.250   1.1530   0.07537   0.06554  -0.0613   0.0476   1.0000
  11.500   1.1499   0.07904   0.06930  -0.0614   0.0453   1.0000
  11.750   1.1471   0.08251   0.07278  -0.0611   0.0432   1.0000
  12.000   1.1498   0.08529   0.07568  -0.0604   0.0409   1.0000
  12.250   1.1553   0.08772   0.07829  -0.0594   0.0388   1.0000
  12.500   1.1637   0.08965   0.08036  -0.0578   0.0372   1.0000
  12.750   1.1743   0.09133   0.08216  -0.0559   0.0358   1.0000
  13.000   1.1882   0.09256   0.08342  -0.0535   0.0343   1.0000
  13.250   1.1957   0.09541   0.08655  -0.0526   0.0332   1.0000
  13.500   1.1976   0.09918   0.09063  -0.0528   0.0322   1.0000
  13.750   1.1963   0.10348   0.09527  -0.0536   0.0313   1.0000
  14.000   1.1924   0.10827   0.10030  -0.0550   0.0307   1.0000
  14.250   1.1861   0.11358   0.10585  -0.0570   0.0304   1.0000
  14.500   1.1778   0.11946   0.11197  -0.0596   0.0302   1.0000
  14.750   1.1673   0.12601   0.11874  -0.0629   0.0302   1.0000
  15.000   1.1550   0.13327   0.12622  -0.0670   0.0303   1.0000
  15.250   1.1415   0.14131   0.13445  -0.0719   0.0305   1.0000
  15.500   1.1273   0.15015   0.14346  -0.0775   0.0308   1.0000
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