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S8064 (s8064-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 100,000
Max Cl/Cd: 46.43 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8064-il-100000-n5.txt
Download as CSV file: xf-s8064-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5239   0.09509   0.09012  -0.0475   1.0000   0.0206
 -11.500  -0.5413   0.08517   0.08023  -0.0530   1.0000   0.0200
 -11.250  -0.5718   0.07388   0.06890  -0.0612   1.0000   0.0194
 -11.000  -0.6011   0.06633   0.06121  -0.0662   1.0000   0.0189
 -10.750  -0.6297   0.06097   0.05570  -0.0679   1.0000   0.0187
 -10.500  -0.6605   0.05714   0.05173  -0.0664   1.0000   0.0183
 -10.250  -0.6919   0.05501   0.04947  -0.0617   1.0000   0.0181
 -10.000  -0.7215   0.05381   0.04819  -0.0555   1.0000   0.0181
  -9.750  -0.7495   0.05245   0.04669  -0.0488   1.0000   0.0180
  -9.500  -0.7699   0.05049   0.04454  -0.0434   1.0000   0.0180
  -9.250  -0.7712   0.04753   0.04127  -0.0418   0.9962   0.0182
  -9.000  -0.7664   0.04414   0.03743  -0.0409   0.9915   0.0183
  -8.750  -0.7567   0.04116   0.03405  -0.0400   0.9873   0.0186
  -8.500  -0.7414   0.03837   0.03086  -0.0397   0.9842   0.0189
  -8.250  -0.7271   0.03597   0.02810  -0.0385   0.9805   0.0195
  -8.000  -0.7088   0.03381   0.02559  -0.0377   0.9772   0.0200
  -7.750  -0.6868   0.03176   0.02323  -0.0374   0.9745   0.0208
  -7.500  -0.6618   0.02992   0.02110  -0.0375   0.9723   0.0219
  -7.250  -0.6421   0.02837   0.01938  -0.0366   0.9692   0.0235
  -7.000  -0.6229   0.02739   0.01833  -0.0359   0.9655   0.0260
  -6.750  -0.5995   0.02632   0.01706  -0.0356   0.9625   0.0298
  -6.500  -0.5765   0.02505   0.01576  -0.0355   0.9597   0.0338
  -6.250  -0.5554   0.02403   0.01466  -0.0347   0.9565   0.0412
  -6.000  -0.5379   0.02325   0.01389  -0.0334   0.9522   0.0533
  -5.750  -0.5151   0.02249   0.01313  -0.0331   0.9488   0.0715
  -5.500  -0.4898   0.02168   0.01238  -0.0332   0.9459   0.0948
  -5.250  -0.4686   0.02099   0.01178  -0.0326   0.9423   0.1220
  -5.000  -0.4515   0.02036   0.01128  -0.0310   0.9376   0.1583
  -4.750  -0.4288   0.01960   0.01077  -0.0308   0.9340   0.2179
  -4.500  -0.4051   0.01873   0.01036  -0.0308   0.9312   0.3139
  -4.250  -0.3929   0.01809   0.01016  -0.0281   0.9259   0.4120
  -4.000  -0.3742   0.01764   0.01009  -0.0264   0.9215   0.5087
  -3.750  -0.3477   0.01744   0.01013  -0.0259   0.9185   0.5889
  -3.500  -0.3166   0.01751   0.01034  -0.0259   0.9163   0.6507
  -3.250  -0.3034   0.01764   0.01046  -0.0227   0.9098   0.6886
  -3.000  -0.2769   0.01780   0.01056  -0.0221   0.9059   0.7228
  -2.750  -0.2460   0.01797   0.01062  -0.0223   0.9032   0.7511
  -2.500  -0.2259   0.01815   0.01074  -0.0204   0.8980   0.7732
  -2.250  -0.2037   0.01830   0.01082  -0.0190   0.8929   0.7945
  -2.000  -0.1718   0.01849   0.01092  -0.0192   0.8899   0.8125
  -1.750  -0.1380   0.01863   0.01097  -0.0200   0.8876   0.8277
  -1.500  -0.1231   0.01874   0.01104  -0.0174   0.8801   0.8414
  -1.250  -0.0931   0.01880   0.01102  -0.0177   0.8763   0.8534
  -1.000  -0.0554   0.01888   0.01102  -0.0195   0.8739   0.8618
  -0.750  -0.0351   0.01897   0.01108  -0.0181   0.8672   0.8723
  -0.500  -0.0062   0.01900   0.01105  -0.0183   0.8626   0.8823
  -0.250   0.0338   0.01905   0.01105  -0.0206   0.8600   0.8885
   0.000   0.0564   0.01912   0.01110  -0.0198   0.8534   0.8983
   0.250   0.0922   0.01918   0.01115  -0.0215   0.8488   0.9044
   0.500   0.1262   0.01914   0.01109  -0.0227   0.8454   0.9123
   0.750   0.1615   0.01923   0.01119  -0.0244   0.8401   0.9177
   1.000   0.1910   0.01927   0.01124  -0.0250   0.8339   0.9255
   1.250   0.2321   0.01920   0.01120  -0.0276   0.8306   0.9299
   1.500   0.2635   0.01929   0.01133  -0.0287   0.8235   0.9364
   1.750   0.2972   0.01922   0.01131  -0.0299   0.8179   0.9428
   2.000   0.3416   0.01905   0.01121  -0.0330   0.8147   0.9458
   2.250   0.3713   0.01911   0.01135  -0.0339   0.8048   0.9527
   2.500   0.4109   0.01883   0.01116  -0.0359   0.8003   0.9572
   2.750   0.4453   0.01877   0.01121  -0.0375   0.7897   0.9624
   3.000   0.4789   0.01856   0.01110  -0.0386   0.7801   0.9686
   3.250   0.5183   0.01808   0.01075  -0.0404   0.7718   0.9727
   3.500   0.5533   0.01772   0.01051  -0.0416   0.7581   0.9781
   3.750   0.5852   0.01736   0.01027  -0.0422   0.7410   0.9846
   4.000   0.6209   0.01689   0.00993  -0.0433   0.7196   0.9898
   4.250   0.6567   0.01638   0.00950  -0.0442   0.6929   0.9947
   4.500   0.6938   0.01590   0.00900  -0.0452   0.6564   0.9987
   5.000   0.7313   0.01575   0.00864  -0.0410   0.5609   1.0000
   5.250   0.7420   0.01600   0.00864  -0.0376   0.4996   1.0000
   5.500   0.7468   0.01649   0.00877  -0.0334   0.4299   1.0000
   5.750   0.7482   0.01717   0.00906  -0.0288   0.3602   1.0000
   6.000   0.7497   0.01797   0.00948  -0.0244   0.2945   1.0000
   6.250   0.7530   0.01883   0.01001  -0.0205   0.2356   1.0000
   6.500   0.7592   0.01970   0.01059  -0.0172   0.1877   1.0000
   6.750   0.7681   0.02055   0.01123  -0.0143   0.1514   1.0000
   7.000   0.7786   0.02138   0.01193  -0.0117   0.1262   1.0000
   7.250   0.7896   0.02222   0.01269  -0.0092   0.1085   1.0000
   7.500   0.8005   0.02304   0.01347  -0.0067   0.0950   1.0000
   7.750   0.8118   0.02390   0.01436  -0.0043   0.0854   1.0000
   8.000   0.8220   0.02490   0.01530  -0.0019   0.0777   1.0000
   8.250   0.8359   0.02577   0.01627   0.0000   0.0696   1.0000
   8.500   0.8479   0.02686   0.01737   0.0020   0.0634   1.0000
   8.750   0.8623   0.02781   0.01841   0.0036   0.0565   1.0000
   9.000   0.8756   0.02896   0.01959   0.0053   0.0506   1.0000
   9.250   0.8894   0.02996   0.02070   0.0068   0.0446   1.0000
   9.500   0.9027   0.03126   0.02207   0.0084   0.0400   1.0000
   9.750   0.9175   0.03257   0.02352   0.0098   0.0361   1.0000
  10.000   0.9298   0.03403   0.02500   0.0112   0.0334   1.0000
  10.250   0.9461   0.03582   0.02699   0.0124   0.0308   1.0000
  10.500   0.9595   0.03738   0.02877   0.0138   0.0282   1.0000
  10.750   0.9696   0.03888   0.03037   0.0153   0.0264   1.0000
  11.000   0.9794   0.04073   0.03229   0.0166   0.0252   1.0000
  11.250   0.9896   0.04325   0.03510   0.0181   0.0242   1.0000
  11.500   0.9958   0.04589   0.03810   0.0197   0.0235   1.0000
  11.750   0.9966   0.04880   0.04135   0.0217   0.0229   1.0000
  12.000   0.9926   0.05191   0.04480   0.0236   0.0224   1.0000
  12.250   0.9850   0.05522   0.04841   0.0253   0.0221   1.0000
  12.500   0.9735   0.05885   0.05234   0.0267   0.0219   1.0000
  12.750   0.9594   0.06276   0.05651   0.0275   0.0216   1.0000
  13.000   0.9420   0.06727   0.06128   0.0276   0.0215   1.0000
  13.250   0.9226   0.07230   0.06656   0.0267   0.0215   1.0000
  13.500   0.8991   0.07850   0.07300   0.0246   0.0218   1.0000
  13.750   0.8719   0.08599   0.08069   0.0209   0.0218   1.0000
  14.000   0.8424   0.09520   0.09009   0.0153   0.0223   1.0000
  14.250   0.8096   0.10707   0.10209   0.0076   0.0229   1.0000
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