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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 500,000
Max Cl/Cd: 95.16 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9037-il-500000-n5.txt
Download as CSV file: xf-s9037-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3469   0.09696   0.09467  -0.0322   1.0000   0.0099
  -9.000  -0.3444   0.09356   0.09129  -0.0333   1.0000   0.0099
  -8.000  -0.3518   0.07945   0.07735  -0.0367   0.9991   0.0102
  -7.750  -0.3371   0.07736   0.07527  -0.0391   0.9901   0.0108
  -7.500  -0.3206   0.07286   0.07077  -0.0455   0.9816   0.0110
  -7.250  -0.2378   0.04941   0.04736  -0.0575   0.9425   0.0095
  -7.000  -0.2391   0.04517   0.04309  -0.0612   0.9261   0.0092
  -6.750  -0.2388   0.03992   0.03777  -0.0660   0.9124   0.0088
  -6.500  -0.2562   0.03887   0.03622  -0.0831   0.9238   0.0067
  -6.250  -0.2452   0.03261   0.02960  -0.0850   0.9120   0.0065
  -6.000  -0.2323   0.02641   0.02288  -0.0856   0.9013   0.0062
  -5.750  -0.2150   0.02180   0.01770  -0.0854   0.8920   0.0060
  -5.500  -0.1940   0.01857   0.01391  -0.0848   0.8840   0.0059
  -5.250  -0.1704   0.01638   0.01128  -0.0842   0.8756   0.0057
  -5.000  -0.1456   0.01477   0.00932  -0.0836   0.8677   0.0057
  -4.750  -0.1202   0.01357   0.00786  -0.0831   0.8591   0.0057
  -4.500  -0.0943   0.01263   0.00670  -0.0826   0.8501   0.0058
  -4.250  -0.0682   0.01188   0.00579  -0.0821   0.8411   0.0058
  -4.000  -0.0419   0.01124   0.00501  -0.0817   0.8315   0.0059
  -3.750  -0.0152   0.01070   0.00435  -0.0814   0.8222   0.0061
  -3.500   0.0116   0.01026   0.00380  -0.0811   0.8129   0.0064
  -3.250   0.0387   0.00991   0.00332  -0.0808   0.8028   0.0067
  -3.000   0.0658   0.00955   0.00287  -0.0805   0.7924   0.0074
  -2.750   0.0931   0.00931   0.00254  -0.0802   0.7815   0.0089
  -2.500   0.1203   0.00907   0.00225  -0.0800   0.7703   0.0127
  -2.250   0.1475   0.00884   0.00202  -0.0797   0.7587   0.0274
  -2.000   0.1745   0.00857   0.00185  -0.0796   0.7470   0.0607
  -1.750   0.2015   0.00829   0.00172  -0.0795   0.7353   0.1134
  -1.500   0.2285   0.00808   0.00161  -0.0794   0.7239   0.1635
  -1.250   0.2555   0.00788   0.00152  -0.0792   0.7121   0.2225
  -1.000   0.2825   0.00769   0.00146  -0.0791   0.6997   0.2875
  -0.750   0.3092   0.00749   0.00141  -0.0790   0.6860   0.3657
  -0.500   0.3357   0.00730   0.00138  -0.0788   0.6717   0.4448
  -0.250   0.3617   0.00703   0.00138  -0.0785   0.6575   0.5572
   0.000   0.3867   0.00675   0.00140  -0.0779   0.6435   0.6768
   0.250   0.4092   0.00645   0.00144  -0.0765   0.6296   0.8058
   0.500   0.4320   0.00628   0.00147  -0.0748   0.6159   0.9251
   0.750   0.4744   0.00632   0.00143  -0.0778   0.5998   0.9914
   1.000   0.5038   0.00642   0.00144  -0.0782   0.5845   1.0000
   1.250   0.5299   0.00655   0.00147  -0.0778   0.5678   1.0000
   1.500   0.5559   0.00670   0.00151  -0.0774   0.5488   1.0000
   1.750   0.5819   0.00687   0.00156  -0.0770   0.5296   1.0000
   2.000   0.6081   0.00703   0.00162  -0.0767   0.5118   1.0000
   2.250   0.6344   0.00719   0.00170  -0.0764   0.4948   1.0000
   2.500   0.6606   0.00736   0.00179  -0.0761   0.4781   1.0000
   2.750   0.6867   0.00754   0.00188  -0.0757   0.4607   1.0000
   3.000   0.7125   0.00775   0.00200  -0.0754   0.4400   1.0000
   3.250   0.7382   0.00798   0.00214  -0.0750   0.4189   1.0000
   3.500   0.7641   0.00820   0.00227  -0.0747   0.4000   1.0000
   3.750   0.7900   0.00841   0.00241  -0.0744   0.3828   1.0000
   4.000   0.8158   0.00864   0.00257  -0.0741   0.3659   1.0000
   4.250   0.8414   0.00888   0.00276  -0.0737   0.3483   1.0000
   4.750   0.8926   0.00938   0.00314  -0.0731   0.3154   1.0000
   5.000   0.9176   0.00968   0.00336  -0.0727   0.2940   1.0000
   5.250   0.9423   0.01001   0.00361  -0.0722   0.2725   1.0000
   5.500   0.9672   0.01032   0.00386  -0.0718   0.2536   1.0000
   5.750   0.9921   0.01063   0.00412  -0.0714   0.2383   1.0000
   6.000   1.0164   0.01098   0.00442  -0.0709   0.2209   1.0000
   6.250   1.0407   0.01133   0.00472  -0.0705   0.2030   1.0000
   6.500   1.0650   0.01168   0.00503  -0.0700   0.1884   1.0000
   6.750   1.0887   0.01207   0.00537  -0.0695   0.1715   1.0000
   7.000   1.1115   0.01255   0.00576  -0.0688   0.1521   1.0000
   7.250   1.1346   0.01298   0.00616  -0.0682   0.1361   1.0000
   7.500   1.1574   0.01343   0.00657  -0.0675   0.1215   1.0000
   7.750   1.1801   0.01388   0.00699  -0.0669   0.1100   1.0000
   8.000   1.2024   0.01435   0.00744  -0.0661   0.0988   1.0000
   8.250   1.2240   0.01486   0.00792  -0.0653   0.0859   1.0000
   8.500   1.2447   0.01544   0.00846  -0.0644   0.0714   1.0000
   8.750   1.2651   0.01603   0.00901  -0.0635   0.0606   1.0000
   9.000   1.2847   0.01665   0.00961  -0.0624   0.0504   1.0000
   9.250   1.3036   0.01731   0.01023  -0.0613   0.0406   1.0000
   9.500   1.3226   0.01792   0.01085  -0.0601   0.0336   1.0000
   9.750   1.3405   0.01859   0.01152  -0.0588   0.0276   1.0000
  10.000   1.3572   0.01930   0.01226  -0.0574   0.0228   1.0000
  10.250   1.3742   0.01994   0.01295  -0.0560   0.0195   1.0000
  10.500   1.3870   0.02071   0.01374  -0.0539   0.0157   1.0000
  10.750   1.3994   0.02146   0.01454  -0.0518   0.0123   1.0000
  11.000   1.4092   0.02237   0.01548  -0.0495   0.0089   1.0000
  11.250   1.4170   0.02344   0.01658  -0.0470   0.0061   1.0000
  11.500   1.4249   0.02454   0.01774  -0.0447   0.0049   1.0000
  11.750   1.4334   0.02562   0.01893  -0.0427   0.0042   1.0000
  12.000   1.4407   0.02685   0.02025  -0.0406   0.0037   1.0000
  12.250   1.4473   0.02817   0.02170  -0.0387   0.0034   1.0000
  12.500   1.4528   0.02963   0.02327  -0.0369   0.0032   1.0000
  12.750   1.4555   0.03141   0.02517  -0.0352   0.0030   1.0000
  13.000   1.4591   0.03320   0.02709  -0.0337   0.0029   1.0000
  13.250   1.4626   0.03507   0.02909  -0.0325   0.0028   1.0000
  13.500   1.4643   0.03722   0.03137  -0.0314   0.0027   1.0000
  13.750   1.4645   0.03964   0.03393  -0.0306   0.0026   1.0000
  14.000   1.4643   0.04223   0.03666  -0.0300   0.0025   1.0000
  14.250   1.4616   0.04524   0.03980  -0.0297   0.0024   1.0000
  14.500   1.4581   0.04851   0.04322  -0.0298   0.0024   1.0000
  14.750   1.4532   0.05214   0.04699  -0.0302   0.0023   1.0000
  15.000   1.4464   0.05620   0.05121  -0.0310   0.0023   1.0000
  15.250   1.4390   0.06060   0.05575  -0.0322   0.0023   1.0000
  15.500   1.4301   0.06542   0.06073  -0.0338   0.0022   1.0000
  15.750   1.4192   0.07085   0.06631  -0.0358   0.0022   1.0000
  16.000   1.4071   0.07673   0.07234  -0.0383   0.0021   1.0000
  16.250   1.3942   0.08295   0.07872  -0.0411   0.0021   1.0000
  16.500   1.3803   0.08965   0.08559  -0.0443   0.0021   1.0000
  16.750   1.3653   0.09677   0.09286  -0.0478   0.0021   1.0000
  17.000   1.3491   0.10431   0.10055  -0.0516   0.0021   1.0000
  17.250   1.3327   0.11211   0.10849  -0.0557   0.0021   1.0000
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