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S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8065 (11% version of S8064) (s8065-il)
Reynolds number: 50,000
Max Cl/Cd: 31.82 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8065-il-50000.txt
Download as CSV file: xf-s8065-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8065 (11% version of S8064)                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6214   0.06927   0.06284  -0.0398   1.0000   0.1308
  -7.750  -0.6544   0.06496   0.05818  -0.0369   1.0000   0.1193
  -7.500  -0.6565   0.06125   0.05440  -0.0345   1.0000   0.1168
  -7.250  -0.6632   0.05747   0.05039  -0.0318   1.0000   0.1132
  -7.000  -0.6774   0.05353   0.04564  -0.0281   1.0000   0.1062
  -6.750  -0.6724   0.04992   0.04176  -0.0257   1.0000   0.1054
  -6.500  -0.6654   0.04642   0.03793  -0.0233   1.0000   0.1042
  -6.250  -0.6566   0.04302   0.03407  -0.0208   1.0000   0.1037
  -6.000  -0.6447   0.03999   0.03049  -0.0184   1.0000   0.1050
  -5.750  -0.6298   0.03722   0.02748  -0.0166   1.0000   0.1107
  -5.500  -0.6124   0.03485   0.02469  -0.0146   1.0000   0.1182
  -5.250  -0.5933   0.03251   0.02218  -0.0130   1.0000   0.1298
  -5.000  -0.5725   0.03033   0.01974  -0.0113   1.0000   0.1468
  -4.750  -0.5509   0.02828   0.01773  -0.0098   1.0000   0.1725
  -4.500  -0.5291   0.02639   0.01601  -0.0083   1.0000   0.2100
  -4.250  -0.5090   0.02445   0.01449  -0.0065   1.0000   0.2716
  -4.000  -0.4965   0.02193   0.01324  -0.0035   1.0000   0.4123
  -3.750  -0.4996   0.02108   0.01408   0.0065   1.0000   0.6768
  -3.500  -0.4939   0.02199   0.01502   0.0152   1.0000   0.7892
  -3.250  -0.4548   0.02366   0.01629   0.0193   1.0000   0.8751
  -3.000  -0.1396   0.02606   0.01669  -0.0269   1.0000   0.9876
  -2.750  -0.0987   0.02523   0.01555  -0.0322   1.0000   1.0000
  -2.500  -0.1016   0.02479   0.01502  -0.0291   1.0000   1.0000
  -2.250  -0.1044   0.02438   0.01453  -0.0260   1.0000   1.0000
  -2.000  -0.1071   0.02400   0.01407  -0.0228   1.0000   1.0000
  -1.750  -0.1096   0.02366   0.01366  -0.0194   1.0000   1.0000
  -1.500  -0.1118   0.02335   0.01327  -0.0160   1.0000   1.0000
  -1.250  -0.1138   0.02307   0.01291  -0.0125   1.0000   1.0000
  -1.000  -0.1154   0.02281   0.01257  -0.0090   1.0000   1.0000
  -0.750  -0.1162   0.02259   0.01225  -0.0055   1.0000   1.0000
  -0.500  -0.1152   0.02242   0.01198  -0.0022   1.0000   1.0000
  -0.250  -0.1114   0.02233   0.01179   0.0006   1.0000   1.0000
   0.000  -0.1047   0.02232   0.01167   0.0030   1.0000   1.0000
   0.250  -0.0952   0.02241   0.01166   0.0050   1.0000   1.0000
   0.500  -0.0835   0.02259   0.01173   0.0066   1.0000   1.0000
   0.750  -0.0701   0.02284   0.01187   0.0079   1.0000   1.0000
   1.000  -0.0556   0.02315   0.01209   0.0089   1.0000   1.0000
   1.250  -0.0402   0.02351   0.01239   0.0099   1.0000   1.0000
   1.500  -0.0245   0.02392   0.01275   0.0106   1.0000   1.0000
   1.750  -0.0084   0.02439   0.01317   0.0113   1.0000   1.0000
   2.000   0.0079   0.02490   0.01365   0.0119   1.0000   1.0000
   2.250   0.0244   0.02547   0.01420   0.0124   1.0000   1.0000
   2.500   0.0407   0.02608   0.01480   0.0128   1.0000   1.0000
   2.750   0.0571   0.02675   0.01548   0.0132   1.0000   1.0000
   3.000   0.0733   0.02747   0.01622   0.0134   1.0000   1.0000
   3.250   0.1076   0.02882   0.01764   0.0101   0.9917   1.0000
   3.500   0.1630   0.03082   0.01977   0.0029   0.9718   1.0000
   3.750   0.2084   0.03233   0.02145  -0.0022   0.9507   1.0000
   4.000   0.2607   0.03402   0.02331  -0.0081   0.9287   1.0000
   4.250   0.3007   0.03515   0.02463  -0.0115   0.9048   1.0000
   4.500   0.3437   0.03622   0.02595  -0.0149   0.8795   1.0000
   4.750   0.3899   0.03707   0.02706  -0.0184   0.8524   1.0000
   5.000   0.4383   0.03751   0.02780  -0.0214   0.8230   1.0000
   5.250   0.4991   0.03711   0.02786  -0.0249   0.7899   1.0000
   5.500   0.5630   0.03536   0.02660  -0.0269   0.7511   1.0000
   5.750   0.6683   0.02929   0.02144  -0.0290   0.7010   1.0000
   6.000   0.7250   0.02444   0.01707  -0.0245   0.6241   1.0000
   6.250   0.7439   0.02338   0.01478  -0.0164   0.4153   1.0000
   6.500   0.7464   0.02587   0.01598  -0.0117   0.2984   1.0000
   6.750   0.7714   0.02830   0.01783  -0.0107   0.2344   1.0000
   7.000   0.8038   0.03063   0.01995  -0.0108   0.1967   1.0000
   7.250   0.8344   0.03306   0.02228  -0.0108   0.1715   1.0000
   7.500   0.8621   0.03572   0.02518  -0.0103   0.1553   1.0000
   7.750   0.8838   0.03837   0.02803  -0.0091   0.1413   1.0000
   8.000   0.9061   0.04154   0.03134  -0.0082   0.1315   1.0000
   8.250   0.9195   0.04428   0.03452  -0.0060   0.1228   1.0000
   8.500   0.9330   0.04789   0.03842  -0.0042   0.1174   1.0000
   8.750   0.9374   0.05150   0.04261  -0.0013   0.1152   1.0000
   9.000   0.9384   0.05507   0.04665   0.0015   0.1127   1.0000
   9.250   0.9402   0.05854   0.05042   0.0039   0.1095   1.0000
   9.500   0.9356   0.06252   0.05475   0.0065   0.1091   1.0000
   9.750   0.9173   0.06689   0.05953   0.0095   0.1113   1.0000
  10.000   0.8979   0.07129   0.06419   0.0120   0.1136   1.0000
  10.250   0.8783   0.07550   0.06854   0.0141   0.1155   1.0000
  10.500   0.8647   0.08019   0.07330   0.0151   0.1175   1.0000
  10.750   0.8411   0.08510   0.07834   0.0150   0.1208   1.0000
  11.000   0.7881   0.09396   0.08724   0.0102   0.1310   1.0000
  11.250   0.7935   0.09973   0.09304   0.0095   0.1333   1.0000
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