Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S4310 (s4310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.91 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4310-il-1000000-n5.txt
Download as CSV file: xf-s4310-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3643   0.13633   0.13461  -0.0218   1.0000   0.0042
 -12.500  -0.3549   0.13428   0.13258  -0.0229   1.0000   0.0045
 -10.500  -0.6630   0.02789   0.02504  -0.0846   0.8536   0.0047
 -10.250  -0.6539   0.02468   0.02146  -0.0845   0.8434   0.0048
 -10.000  -0.6363   0.02294   0.01949  -0.0842   0.8349   0.0049
  -9.750  -0.6180   0.02119   0.01748  -0.0838   0.8263   0.0050
  -9.500  -0.5961   0.02007   0.01619  -0.0835   0.8186   0.0052
  -9.000  -0.5517   0.01769   0.01336  -0.0829   0.8033   0.0055
  -8.500  -0.5038   0.01584   0.01115  -0.0824   0.7888   0.0057
  -8.250  -0.4788   0.01512   0.01026  -0.0821   0.7815   0.0059
  -8.000  -0.4533   0.01445   0.00944  -0.0819   0.7746   0.0060
  -7.750  -0.4273   0.01391   0.00876  -0.0817   0.7674   0.0060
  -7.500  -0.4020   0.01308   0.00778  -0.0815   0.7606   0.0064
  -7.250  -0.3755   0.01262   0.00723  -0.0813   0.7536   0.0067
  -7.000  -0.3486   0.01221   0.00675  -0.0812   0.7472   0.0069
  -6.750  -0.3215   0.01188   0.00634  -0.0811   0.7401   0.0072
  -6.500  -0.2943   0.01156   0.00594  -0.0810   0.7338   0.0076
  -6.250  -0.2670   0.01123   0.00552  -0.0809   0.7269   0.0079
  -6.000  -0.2396   0.01093   0.00514  -0.0808   0.7207   0.0084
  -5.750  -0.2120   0.01066   0.00480  -0.0807   0.7141   0.0087
  -5.250  -0.1565   0.01020   0.00427  -0.0806   0.7015   0.0101
  -5.000  -0.1287   0.01000   0.00402  -0.0806   0.6950   0.0107
  -4.750  -0.1008   0.00979   0.00375  -0.0805   0.6891   0.0114
  -4.500  -0.0728   0.00961   0.00351  -0.0805   0.6825   0.0118
  -4.250  -0.0451   0.00933   0.00318  -0.0804   0.6766   0.0127
  -4.000  -0.0169   0.00916   0.00299  -0.0805   0.6702   0.0135
  -3.500   0.0394   0.00890   0.00265  -0.0805   0.6579   0.0154
  -3.250   0.0676   0.00880   0.00250  -0.0805   0.6514   0.0160
  -3.000   0.0956   0.00856   0.00221  -0.0804   0.6454   0.0171
  -2.750   0.1237   0.00841   0.00203  -0.0804   0.6388   0.0185
  -2.500   0.1519   0.00830   0.00188  -0.0804   0.6326   0.0196
  -2.250   0.1803   0.00819   0.00173  -0.0805   0.6260   0.0206
  -2.000   0.2084   0.00812   0.00161  -0.0804   0.6195   0.0214
  -1.750   0.2368   0.00801   0.00148  -0.0805   0.6127   0.0242
  -1.250   0.2932   0.00780   0.00130  -0.0805   0.5982   0.0456
  -1.000   0.3211   0.00768   0.00123  -0.0805   0.5902   0.0743
  -0.750   0.3491   0.00753   0.00119  -0.0806   0.5819   0.1147
  -0.500   0.3770   0.00739   0.00115  -0.0807   0.5736   0.1621
  -0.250   0.4049   0.00727   0.00113  -0.0807   0.5647   0.2084
   0.000   0.4327   0.00713   0.00113  -0.0808   0.5562   0.2684
   0.250   0.4603   0.00701   0.00114  -0.0808   0.5473   0.3340
   0.500   0.4879   0.00684   0.00116  -0.0809   0.5385   0.4123
   0.750   0.5143   0.00648   0.00121  -0.0809   0.5297   0.5721
   1.000   0.5407   0.00624   0.00126  -0.0806   0.5199   0.6903
   1.250   0.5663   0.00606   0.00133  -0.0802   0.5103   0.7878
   1.500   0.5896   0.00593   0.00141  -0.0790   0.5000   0.8793
   1.750   0.6132   0.00593   0.00147  -0.0778   0.4888   0.9391
   2.000   0.6473   0.00600   0.00151  -0.0791   0.4754   0.9768
   2.250   0.6841   0.00613   0.00156  -0.0811   0.4608   0.9996
   2.500   0.7110   0.00627   0.00163  -0.0810   0.4473   1.0000
   2.750   0.7378   0.00642   0.00171  -0.0808   0.4336   1.0000
   3.000   0.7644   0.00659   0.00180  -0.0806   0.4186   1.0000
   3.250   0.7909   0.00677   0.00191  -0.0804   0.4032   1.0000
   3.500   0.8174   0.00696   0.00202  -0.0803   0.3880   1.0000
   3.750   0.8437   0.00717   0.00215  -0.0801   0.3721   1.0000
   4.000   0.8700   0.00738   0.00228  -0.0799   0.3558   1.0000
   4.250   0.8961   0.00760   0.00244  -0.0797   0.3396   1.0000
   4.500   0.9221   0.00783   0.00260  -0.0794   0.3232   1.0000
   4.750   0.9479   0.00808   0.00276  -0.0792   0.3073   1.0000
   5.000   0.9735   0.00834   0.00295  -0.0789   0.2910   1.0000
   5.250   0.9991   0.00859   0.00314  -0.0787   0.2764   1.0000
   5.500   1.0244   0.00887   0.00335  -0.0784   0.2615   1.0000
   5.750   1.0498   0.00913   0.00355  -0.0781   0.2484   1.0000
   6.000   1.0748   0.00941   0.00378  -0.0777   0.2344   1.0000
   6.250   1.0997   0.00969   0.00401  -0.0774   0.2218   1.0000
   6.500   1.1242   0.00999   0.00426  -0.0770   0.2085   1.0000
   6.750   1.1487   0.01029   0.00451  -0.0766   0.1972   1.0000
   7.000   1.1729   0.01060   0.00478  -0.0762   0.1860   1.0000
   7.500   1.2195   0.01132   0.00538  -0.0751   0.1602   1.0000
   7.750   1.2420   0.01172   0.00572  -0.0744   0.1467   1.0000
   8.000   1.2640   0.01213   0.00608  -0.0737   0.1338   1.0000
   8.250   1.2861   0.01252   0.00643  -0.0729   0.1231   1.0000
   8.500   1.3072   0.01295   0.00682  -0.0721   0.1113   1.0000
   8.750   1.3266   0.01348   0.00726  -0.0710   0.0977   1.0000
   9.000   1.3461   0.01396   0.00770  -0.0699   0.0868   1.0000
   9.250   1.3644   0.01449   0.00819  -0.0686   0.0761   1.0000
   9.500   1.3817   0.01503   0.00868  -0.0672   0.0666   1.0000
   9.750   1.3968   0.01560   0.00921  -0.0654   0.0580   1.0000
  10.000   1.4082   0.01622   0.00979  -0.0630   0.0494   1.0000
  10.250   1.4207   0.01680   0.01036  -0.0608   0.0429   1.0000
  10.500   1.4303   0.01756   0.01108  -0.0584   0.0350   1.0000
  10.750   1.4394   0.01840   0.01191  -0.0560   0.0277   1.0000
  11.000   1.4476   0.01934   0.01282  -0.0537   0.0209   1.0000
  11.250   1.4518   0.02059   0.01403  -0.0512   0.0126   1.0000
  11.500   1.4539   0.02206   0.01548  -0.0486   0.0052   1.0000
  11.750   1.4618   0.02322   0.01669  -0.0468   0.0037   1.0000
  12.000   1.4723   0.02426   0.01778  -0.0454   0.0034   1.0000
  12.250   1.4822   0.02537   0.01895  -0.0440   0.0031   1.0000
  12.500   1.4918   0.02655   0.02020  -0.0428   0.0030   1.0000
  12.750   1.4998   0.02790   0.02162  -0.0415   0.0027   1.0000
  13.000   1.5075   0.02932   0.02310  -0.0403   0.0026   1.0000
  13.250   1.5146   0.03084   0.02470  -0.0392   0.0025   1.0000
  13.500   1.5198   0.03258   0.02651  -0.0382   0.0023   1.0000
  13.750   1.5244   0.03445   0.02846  -0.0372   0.0021   1.0000
  14.000   1.5298   0.03628   0.03037  -0.0364   0.0021   1.0000
  14.250   1.5348   0.03821   0.03238  -0.0358   0.0020   1.0000
  14.500   1.5379   0.04040   0.03465  -0.0352   0.0020   1.0000
  14.750   1.5408   0.04267   0.03701  -0.0347   0.0020   1.0000
  15.000   1.5433   0.04508   0.03952  -0.0344   0.0019   1.0000
  15.250   1.5442   0.04775   0.04228  -0.0342   0.0019   1.0000
  15.500   1.5453   0.05049   0.04511  -0.0342   0.0018   1.0000
  15.750   1.5437   0.05366   0.04838  -0.0344   0.0018   1.0000
  16.000   1.5421   0.05694   0.05176  -0.0348   0.0018   1.0000
  16.250   1.5396   0.06045   0.05537  -0.0353   0.0017   1.0000
  16.500   1.5378   0.06397   0.05899  -0.0360   0.0017   1.0000
  16.750   1.5326   0.06809   0.06322  -0.0370   0.0017   1.0000
  17.000   1.5266   0.07247   0.06771  -0.0382   0.0016   1.0000
  17.250   1.5201   0.07705   0.07240  -0.0396   0.0016   1.0000
  17.500   1.5122   0.08196   0.07743  -0.0413   0.0016   1.0000
  17.750   1.5040   0.08709   0.08268  -0.0432   0.0016   1.0000
  18.000   1.4950   0.09248   0.08818  -0.0453   0.0015   1.0000
  18.250   1.4825   0.09862   0.09445  -0.0479   0.0015   1.0000
  18.500   1.4709   0.10473   0.10069  -0.0507   0.0015   1.0000
  18.750   1.4585   0.11114   0.10722  -0.0537   0.0015   1.0000
  19.000   1.4463   0.11760   0.11380  -0.0568   0.0015   1.0000
  19.250   1.4336   0.12429   0.12061  -0.0602   0.0015   1.0000
<< Back to S4310 (s4310-il)

Polar data table (+)

Polar graphs


<< Back to S4310 (s4310-il)