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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 100,000
Max Cl/Cd: 52.69 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9000-il-100000-n5.txt
Download as CSV file: xf-s9000-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4305   0.08982   0.08478  -0.0287   1.0000   0.0189
  -8.500  -0.4329   0.08579   0.08082  -0.0302   1.0000   0.0185
  -8.250  -0.4376   0.08158   0.07670  -0.0317   1.0000   0.0180
  -8.000  -0.4458   0.07723   0.07245  -0.0333   1.0000   0.0177
  -7.750  -0.4583   0.07226   0.06758  -0.0358   1.0000   0.0171
  -7.500  -0.4717   0.06111   0.05632  -0.0444   1.0000   0.0157
  -7.250  -0.4760   0.05648   0.05161  -0.0457   1.0000   0.0156
  -7.000  -0.4771   0.05222   0.04721  -0.0465   1.0000   0.0155
  -6.750  -0.4755   0.04791   0.04268  -0.0469   1.0000   0.0154
  -6.500  -0.4709   0.04348   0.03794  -0.0470   1.0000   0.0153
  -6.250  -0.4621   0.03940   0.03346  -0.0468   1.0000   0.0153
  -6.000  -0.4493   0.03548   0.02896  -0.0464   1.0000   0.0157
  -5.750  -0.4348   0.03273   0.02596  -0.0459   1.0000   0.0165
  -5.500  -0.4174   0.03122   0.02429  -0.0453   1.0000   0.0180
  -5.250  -0.3981   0.02887   0.02153  -0.0446   1.0000   0.0190
  -5.000  -0.3769   0.02646   0.01862  -0.0438   1.0000   0.0200
  -4.750  -0.3547   0.02440   0.01616  -0.0429   1.0000   0.0207
  -4.500  -0.3318   0.02267   0.01407  -0.0420   1.0000   0.0218
  -4.250  -0.3094   0.02103   0.01230  -0.0413   1.0000   0.0235
  -4.000  -0.2741   0.02003   0.01119  -0.0431   0.9955   0.0289
  -3.750  -0.2388   0.01875   0.00981  -0.0449   0.9904   0.0359
  -3.500  -0.2019   0.01776   0.00874  -0.0469   0.9849   0.0496
  -3.250  -0.1667   0.01682   0.00784  -0.0487   0.9785   0.0744
  -3.000  -0.1301   0.01589   0.00716  -0.0508   0.9722   0.1300
  -2.750  -0.0966   0.01507   0.00675  -0.0525   0.9646   0.2313
  -2.500  -0.0610   0.01433   0.00650  -0.0545   0.9580   0.3651
  -2.250  -0.0305   0.01369   0.00634  -0.0552   0.9491   0.4978
  -2.000   0.0009   0.01320   0.00634  -0.0553   0.9421   0.6413
  -1.750   0.0288   0.01297   0.00628  -0.0544   0.9325   0.7438
  -1.500   0.0570   0.01282   0.00617  -0.0535   0.9228   0.8117
  -1.250   0.0902   0.01265   0.00598  -0.0535   0.9152   0.8664
  -0.750   0.1714   0.01233   0.00548  -0.0574   0.8960   0.9608
  -0.500   0.2226   0.01214   0.00516  -0.0620   0.8875   1.0000
  -0.250   0.2553   0.01208   0.00495  -0.0629   0.8740   1.0000
   0.000   0.2880   0.01202   0.00477  -0.0638   0.8599   1.0000
   0.250   0.3206   0.01197   0.00461  -0.0646   0.8448   1.0000
   0.500   0.3515   0.01195   0.00448  -0.0650   0.8282   1.0000
   0.750   0.3811   0.01196   0.00439  -0.0651   0.8102   1.0000
   1.000   0.4106   0.01199   0.00433  -0.0652   0.7921   1.0000
   1.250   0.4401   0.01203   0.00428  -0.0652   0.7736   1.0000
   1.500   0.4677   0.01211   0.00428  -0.0650   0.7530   1.0000
   1.750   0.4955   0.01220   0.00428  -0.0647   0.7318   1.0000
   2.000   0.5223   0.01232   0.00431  -0.0642   0.7094   1.0000
   2.250   0.5493   0.01245   0.00437  -0.0638   0.6871   1.0000
   2.500   0.5753   0.01262   0.00446  -0.0632   0.6635   1.0000
   2.750   0.6014   0.01280   0.00456  -0.0626   0.6398   1.0000
   3.000   0.6271   0.01301   0.00468  -0.0620   0.6153   1.0000
   3.250   0.6524   0.01325   0.00486  -0.0614   0.5888   1.0000
   3.500   0.6774   0.01351   0.00504  -0.0607   0.5619   1.0000
   3.750   0.7021   0.01379   0.00525  -0.0599   0.5347   1.0000
   4.000   0.7268   0.01410   0.00551  -0.0592   0.5081   1.0000
   4.250   0.7511   0.01443   0.00578  -0.0585   0.4816   1.0000
   4.500   0.7753   0.01479   0.00607  -0.0578   0.4548   1.0000
   4.750   0.7991   0.01518   0.00640  -0.0570   0.4270   1.0000
   5.000   0.8225   0.01561   0.00678  -0.0562   0.3988   1.0000
   5.250   0.8457   0.01606   0.00717  -0.0554   0.3704   1.0000
   5.500   0.8686   0.01655   0.00760  -0.0546   0.3428   1.0000
   5.750   0.8915   0.01706   0.00807  -0.0539   0.3161   1.0000
   6.000   0.9142   0.01759   0.00861  -0.0531   0.2906   1.0000
   6.250   0.9365   0.01817   0.00917  -0.0523   0.2657   1.0000
   6.500   0.9584   0.01880   0.00976  -0.0514   0.2419   1.0000
   6.750   0.9798   0.01946   0.01039  -0.0506   0.2176   1.0000
   7.000   1.0012   0.02015   0.01108  -0.0497   0.1948   1.0000
   7.250   1.0217   0.02092   0.01185  -0.0488   0.1739   1.0000
   7.500   1.0425   0.02168   0.01265  -0.0479   0.1543   1.0000
   7.750   1.0622   0.02254   0.01352  -0.0469   0.1367   1.0000
   8.000   1.0815   0.02345   0.01447  -0.0458   0.1225   1.0000
   8.250   1.1001   0.02442   0.01550  -0.0446   0.1093   1.0000
   8.500   1.1180   0.02545   0.01659  -0.0434   0.0968   1.0000
   8.750   1.1352   0.02654   0.01780  -0.0422   0.0861   1.0000
   9.000   1.1510   0.02774   0.01907  -0.0407   0.0770   1.0000
   9.250   1.1648   0.02903   0.02036  -0.0392   0.0687   1.0000
   9.500   1.1805   0.03020   0.02175  -0.0378   0.0607   1.0000
   9.750   1.1923   0.03165   0.02329  -0.0361   0.0546   1.0000
  10.000   1.2043   0.03300   0.02480  -0.0344   0.0485   1.0000
  10.250   1.2117   0.03463   0.02652  -0.0322   0.0440   1.0000
  10.500   1.2195   0.03625   0.02836  -0.0301   0.0398   1.0000
  10.750   1.2234   0.03797   0.03021  -0.0279   0.0365   1.0000
  11.000   1.2265   0.04004   0.03245  -0.0258   0.0335   1.0000
  11.250   1.2299   0.04219   0.03484  -0.0239   0.0309   1.0000
  11.500   1.2310   0.04452   0.03736  -0.0222   0.0291   1.0000
  11.750   1.2299   0.04699   0.03996  -0.0209   0.0276   1.0000
  12.000   1.2257   0.05006   0.04311  -0.0199   0.0262   1.0000
  12.250   1.2224   0.05325   0.04662  -0.0193   0.0249   1.0000
  12.500   1.2169   0.05682   0.05048  -0.0191   0.0236   1.0000
  12.750   1.2094   0.06078   0.05471  -0.0196   0.0227   1.0000
  13.000   1.2000   0.06526   0.05942  -0.0206   0.0220   1.0000
  13.250   1.1888   0.07028   0.06466  -0.0224   0.0215   1.0000
  13.500   1.1759   0.07588   0.07049  -0.0248   0.0212   1.0000
  13.750   1.1608   0.08220   0.07702  -0.0280   0.0210   1.0000
  14.000   1.1434   0.08940   0.08445  -0.0321   0.0210   1.0000
  14.250   1.1224   0.09786   0.09312  -0.0372   0.0211   1.0000
  14.500   1.0973   0.10798   0.10346  -0.0436   0.0215   1.0000
  14.750   1.0674   0.12018   0.11584  -0.0514   0.0223   1.0000
  15.000   1.0325   0.13486   0.13063  -0.0604   0.0238   1.0000
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