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S4053 (s4053-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 50,000
Max Cl/Cd: 38.24 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4053-il-50000.txt
Download as CSV file: xf-s4053-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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  -0.3783   0.09896   0.09228  -0.0219   1.0000   0.2372
  -7.750  -0.3759   0.09592   0.08933  -0.0212   1.0000   0.2469
  -7.500  -0.4002   0.09585   0.08946  -0.0211   1.0000   0.2552
  -7.250  -0.3905   0.09223   0.08589  -0.0194   1.0000   0.2689
  -7.000  -0.3837   0.08895   0.08265  -0.0177   1.0000   0.2818
  -6.750  -0.3825   0.08619   0.07999  -0.0158   1.0000   0.2948
  -6.500  -0.3858   0.08382   0.07774  -0.0137   1.0000   0.3090
  -6.250  -0.3893   0.08156   0.07561  -0.0116   1.0000   0.3243
  -6.000  -0.3991   0.07979   0.07397  -0.0095   1.0000   0.3413
  -5.750  -0.4083   0.07785   0.07218  -0.0072   1.0000   0.3585
  -5.500  -0.3954   0.07456   0.06893  -0.0031   1.0000   0.3804
  -5.250  -0.4123   0.07336   0.06789   0.0002   1.0000   0.4026
  -5.000  -0.4097   0.07102   0.06562   0.0047   1.0000   0.4288
  -4.000  -0.3525   0.04576   0.03856  -0.0372   1.0000   0.1514
  -3.750  -0.3262   0.04094   0.03292  -0.0388   1.0000   0.1275
  -3.500  -0.3049   0.03822   0.02982  -0.0385   1.0000   0.1219
  -3.250  -0.2826   0.03568   0.02684  -0.0383   1.0000   0.1203
  -3.000  -0.2585   0.03338   0.02405  -0.0380   1.0000   0.1188
  -2.750  -0.2337   0.03135   0.02153  -0.0375   1.0000   0.1166
  -2.500  -0.2094   0.02968   0.01943  -0.0368   1.0000   0.1170
  -2.250  -0.1857   0.02831   0.01775  -0.0359   1.0000   0.1195
  -2.000  -0.1619   0.02718   0.01632  -0.0351   1.0000   0.1269
  -1.750  -0.1399   0.02628   0.01530  -0.0341   1.0000   0.1399
  -1.500  -0.1156   0.02519   0.01428  -0.0333   1.0000   0.1593
  -1.250  -0.0797   0.02006   0.01271  -0.0324   1.0000   1.0000
  -1.000  -0.0591   0.02044   0.01228  -0.0315   1.0000   1.0000
  -0.750  -0.0397   0.02085   0.01222  -0.0309   1.0000   1.0000
  -0.500  -0.0205   0.02130   0.01229  -0.0304   1.0000   1.0000
  -0.250  -0.0015   0.02178   0.01246  -0.0300   1.0000   1.0000
   0.000   0.0174   0.02230   0.01268  -0.0295   1.0000   1.0000
   0.250   0.0362   0.02285   0.01300  -0.0292   1.0000   1.0000
   0.500   0.0548   0.02345   0.01338  -0.0288   1.0000   1.0000
   0.750   0.0732   0.02408   0.01382  -0.0285   1.0000   1.0000
   1.000   0.1021   0.02501   0.01454  -0.0303   0.9955   1.0000
   1.250   0.1473   0.02633   0.01567  -0.0351   0.9839   1.0000
   1.500   0.1883   0.02747   0.01666  -0.0390   0.9718   1.0000
   1.750   0.2265   0.02851   0.01759  -0.0424   0.9592   1.0000
   2.000   0.2641   0.02954   0.01854  -0.0455   0.9462   1.0000
   2.250   0.3011   0.03054   0.01950  -0.0485   0.9326   1.0000
   2.500   0.3374   0.03153   0.02045  -0.0512   0.9188   1.0000
   2.750   0.3739   0.03249   0.02141  -0.0538   0.9044   1.0000
   3.000   0.4107   0.03343   0.02237  -0.0563   0.8895   1.0000
   3.250   0.4490   0.03433   0.02334  -0.0588   0.8740   1.0000
   3.500   0.4874   0.03518   0.02425  -0.0612   0.8581   1.0000
   3.750   0.5148   0.03600   0.02515  -0.0618   0.8407   1.0000
   4.000   0.5465   0.03678   0.02606  -0.0629   0.8226   1.0000
   4.250   0.5852   0.03739   0.02681  -0.0647   0.8045   1.0000
   4.500   0.6343   0.03765   0.02726  -0.0674   0.7866   1.0000
   4.750   0.6561   0.03837   0.02811  -0.0665   0.7652   1.0000
   5.000   0.7075   0.03806   0.02809  -0.0685   0.7451   1.0000
   5.250   0.7421   0.03807   0.02832  -0.0684   0.7227   1.0000
   5.500   0.8038   0.03640   0.02704  -0.0698   0.7014   1.0000
   5.750   0.8394   0.03561   0.02650  -0.0684   0.6760   1.0000
   6.000   0.8852   0.03375   0.02494  -0.0669   0.6488   1.0000
   6.250   0.9330   0.03125   0.02275  -0.0650   0.6172   1.0000
   6.500   0.9684   0.02939   0.02106  -0.0620   0.5787   1.0000
   6.750   1.0002   0.02763   0.01933  -0.0586   0.5311   1.0000
   7.000   1.0225   0.02674   0.01827  -0.0546   0.4719   1.0000
   7.250   1.0353   0.02713   0.01828  -0.0504   0.4040   1.0000
   7.500   1.0464   0.02845   0.01907  -0.0467   0.3383   1.0000
   7.750   1.0597   0.03029   0.02042  -0.0440   0.2846   1.0000
   8.000   1.0770   0.03237   0.02216  -0.0420   0.2432   1.0000
   8.250   1.0969   0.03463   0.02435  -0.0406   0.2126   1.0000
   8.500   1.1216   0.03709   0.02664  -0.0399   0.1885   1.0000
   8.750   1.1391   0.03961   0.02944  -0.0383   0.1709   1.0000
   9.000   1.1589   0.04255   0.03259  -0.0370   0.1572   1.0000
   9.250   1.1748   0.04539   0.03561  -0.0355   0.1444   1.0000
   9.500   1.1956   0.04895   0.03920  -0.0347   0.1337   1.0000
   9.750   1.1934   0.05213   0.04315  -0.0311   0.1277   1.0000
  10.000   1.2100   0.05601   0.04702  -0.0302   0.1198   1.0000
  10.250   1.2009   0.05988   0.05155  -0.0267   0.1175   1.0000
  10.500   1.1895   0.06386   0.05601  -0.0236   0.1153   1.0000
  10.750   1.1759   0.06784   0.06034  -0.0208   0.1134   1.0000
  11.000   1.1567   0.07195   0.06474  -0.0181   0.1130   1.0000
  11.250   1.1298   0.07635   0.06936  -0.0157   0.1142   1.0000
  11.500   1.1016   0.08144   0.07463  -0.0149   0.1163   1.0000
  11.750   1.0764   0.08718   0.08048  -0.0156   0.1180   1.0000
  12.000   1.0550   0.09349   0.08687  -0.0173   0.1192   1.0000
  12.250   1.0369   0.10035   0.09378  -0.0196   0.1201   1.0000
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