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S8064 (s8064-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 100,000
Max Cl/Cd: 48.8 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8064-il-100000.txt
Download as CSV file: xf-s8064-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.7162   0.05226   0.04707  -0.0307   1.0000   0.0687
  -8.000  -0.7523   0.05583   0.05041  -0.0285   1.0000   0.0637
  -7.750  -0.7711   0.05041   0.04415  -0.0228   1.0000   0.0549
  -7.500  -0.7701   0.04664   0.04014  -0.0199   1.0000   0.0534
  -7.250  -0.7669   0.04319   0.03635  -0.0169   1.0000   0.0519
  -7.000  -0.7611   0.03981   0.03251  -0.0138   1.0000   0.0506
  -6.750  -0.7513   0.03672   0.02894  -0.0111   1.0000   0.0502
  -6.500  -0.7374   0.03409   0.02585  -0.0087   1.0000   0.0504
  -6.250  -0.7207   0.03196   0.02335  -0.0068   1.0000   0.0516
  -6.000  -0.7030   0.03048   0.02145  -0.0048   1.0000   0.0553
  -5.750  -0.6838   0.02827   0.01918  -0.0035   1.0000   0.0598
  -5.500  -0.6638   0.02679   0.01756  -0.0019   1.0000   0.0651
  -5.250  -0.6449   0.02522   0.01595  -0.0004   1.0000   0.0743
  -5.000  -0.6273   0.02397   0.01475   0.0013   1.0000   0.0897
  -4.750  -0.6107   0.02278   0.01363   0.0030   1.0000   0.1124
  -4.500  -0.5948   0.02163   0.01267   0.0048   1.0000   0.1416
  -4.250  -0.5800   0.02040   0.01177   0.0067   1.0000   0.1861
  -4.000  -0.5686   0.01871   0.01093   0.0090   1.0000   0.2964
  -3.750  -0.5630   0.01718   0.01080   0.0130   1.0000   0.5366
  -3.500  -0.5524   0.01714   0.01132   0.0175   1.0000   0.6684
  -3.250  -0.5395   0.01745   0.01165   0.0212   1.0000   0.7368
  -3.000  -0.5267   0.01781   0.01197   0.0250   1.0000   0.7822
  -2.750  -0.5139   0.01814   0.01226   0.0289   1.0000   0.8182
  -2.500  -0.5013   0.01845   0.01248   0.0327   1.0000   0.8519
  -2.250  -0.4851   0.01879   0.01274   0.0358   1.0000   0.8833
  -2.000  -0.4422   0.01975   0.01353   0.0338   0.9960   0.9138
  -1.750  -0.3686   0.02124   0.01474   0.0258   0.9926   0.9382
  -1.500  -0.2785   0.02268   0.01590   0.0141   0.9905   0.9565
  -1.250  -0.1975   0.02358   0.01656   0.0032   0.9876   0.9696
  -1.000  -0.1251   0.02415   0.01695  -0.0066   0.9843   0.9792
  -0.750  -0.0635   0.02443   0.01710  -0.0146   0.9799   0.9884
  -0.500  -0.0017   0.02469   0.01725  -0.0226   0.9756   0.9971
  -0.250   0.0444   0.02492   0.01741  -0.0279   0.9697   1.0000
   0.000   0.0718   0.02498   0.01743  -0.0295   0.9608   1.0000
   0.250   0.0986   0.02512   0.01753  -0.0308   0.9518   1.0000
   0.500   0.1367   0.02539   0.01778  -0.0341   0.9445   1.0000
   0.750   0.1557   0.02548   0.01786  -0.0338   0.9339   1.0000
   1.000   0.1803   0.02568   0.01805  -0.0345   0.9242   1.0000
   1.250   0.2189   0.02595   0.01834  -0.0375   0.9167   1.0000
   1.500   0.2360   0.02608   0.01848  -0.0365   0.9050   1.0000
   1.750   0.2568   0.02625   0.01868  -0.0362   0.8941   1.0000
   2.000   0.3048   0.02649   0.01897  -0.0404   0.8875   1.0000
   2.250   0.3200   0.02657   0.01909  -0.0388   0.8749   1.0000
   2.500   0.3368   0.02667   0.01923  -0.0375   0.8625   1.0000
   2.750   0.3581   0.02674   0.01935  -0.0367   0.8507   1.0000
   3.000   0.4083   0.02668   0.01941  -0.0406   0.8429   1.0000
   3.500   0.4620   0.02634   0.01925  -0.0401   0.8180   1.0000
   3.750   0.4936   0.02597   0.01899  -0.0403   0.8051   1.0000
   4.000   0.5396   0.02522   0.01843  -0.0425   0.7925   1.0000
   4.250   0.5944   0.02387   0.01729  -0.0454   0.7793   1.0000
   4.500   0.6415   0.02221   0.01585  -0.0464   0.7647   1.0000
   4.750   0.6830   0.02044   0.01427  -0.0463   0.7485   1.0000
   5.000   0.7212   0.01877   0.01277  -0.0456   0.7299   1.0000
   5.250   0.7425   0.01777   0.01190  -0.0427   0.7040   1.0000
   5.500   0.7639   0.01696   0.01115  -0.0399   0.6687   1.0000
   5.750   0.7861   0.01636   0.01047  -0.0372   0.6143   1.0000
   6.000   0.7979   0.01635   0.01016  -0.0331   0.5316   1.0000
   6.250   0.7959   0.01712   0.01020  -0.0271   0.4107   1.0000
   6.500   0.7848   0.01852   0.01078  -0.0204   0.2982   1.0000
   6.750   0.7786   0.02013   0.01168  -0.0150   0.2216   1.0000
   7.000   0.7819   0.02157   0.01268  -0.0111   0.1788   1.0000
   7.250   0.7924   0.02294   0.01376  -0.0085   0.1520   1.0000
   7.500   0.8099   0.02424   0.01499  -0.0068   0.1319   1.0000
   7.750   0.8305   0.02561   0.01627  -0.0058   0.1158   1.0000
   8.000   0.8562   0.02723   0.01785  -0.0056   0.1027   1.0000
   8.250   0.8810   0.02892   0.01959  -0.0052   0.0907   1.0000
   8.500   0.9054   0.03080   0.02149  -0.0049   0.0800   1.0000
   8.750   0.9324   0.03324   0.02386  -0.0053   0.0705   1.0000
   9.000   0.9509   0.03513   0.02619  -0.0035   0.0651   1.0000
   9.250   0.9719   0.03742   0.02857  -0.0027   0.0603   1.0000
   9.500   0.9858   0.04058   0.03208  -0.0010   0.0569   1.0000
   9.750   0.9934   0.04307   0.03508   0.0019   0.0547   1.0000
  10.000   0.9983   0.04627   0.03872   0.0048   0.0537   1.0000
  10.250   0.9984   0.04966   0.04252   0.0080   0.0535   1.0000
  10.500   0.9928   0.05316   0.04641   0.0115   0.0536   1.0000
  10.750   0.9825   0.05663   0.05020   0.0153   0.0542   1.0000
  11.000   0.9672   0.06003   0.05387   0.0192   0.0547   1.0000
  11.250   0.9503   0.06363   0.05770   0.0224   0.0554   1.0000
  11.500   0.9307   0.06743   0.06170   0.0250   0.0559   1.0000
  11.750   0.9140   0.07148   0.06591   0.0265   0.0566   1.0000
  12.000   0.8938   0.07596   0.07055   0.0274   0.0571   1.0000
  12.250   0.8891   0.08194   0.07655   0.0272   0.0582   1.0000
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