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S4110 (s4110-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4110 (s4110-il)
Reynolds number: 500,000
Max Cl/Cd: 89.88 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4110-il-500000-n5.txt
Download as CSV file: xf-s4110-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4110                                           
  
 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  -0.4373   0.08372   0.08138  -0.0337   1.0000   0.0090
  -9.000  -0.4444   0.07941   0.07711  -0.0351   1.0000   0.0091
  -8.500  -0.5470   0.03214   0.02919  -0.0765   0.9882   0.0084
  -8.250  -0.5232   0.02564   0.02194  -0.0823   0.9841   0.0085
  -8.000  -0.4984   0.02263   0.01848  -0.0842   0.9795   0.0086
  -7.750  -0.4705   0.02042   0.01591  -0.0858   0.9755   0.0087
  -7.500  -0.4400   0.01873   0.01392  -0.0873   0.9727   0.0088
  -7.250  -0.4084   0.01738   0.01232  -0.0889   0.9705   0.0089
  -7.000  -0.3837   0.01563   0.01030  -0.0890   0.9640   0.0092
  -6.750  -0.3539   0.01458   0.00911  -0.0899   0.9599   0.0095
  -6.500  -0.3221   0.01378   0.00819  -0.0910   0.9567   0.0099
  -6.250  -0.2949   0.01313   0.00744  -0.0910   0.9499   0.0102
  -6.000  -0.2643   0.01251   0.00672  -0.0917   0.9451   0.0106
  -5.750  -0.2347   0.01196   0.00608  -0.0922   0.9395   0.0111
  -5.500  -0.2055   0.01146   0.00547  -0.0925   0.9329   0.0115
  -5.250  -0.1757   0.01101   0.00493  -0.0929   0.9269   0.0120
  -5.000  -0.1475   0.01061   0.00446  -0.0929   0.9191   0.0127
  -4.750  -0.1189   0.01018   0.00397  -0.0930   0.9119   0.0141
  -4.500  -0.0910   0.00986   0.00358  -0.0929   0.9035   0.0153
  -4.250  -0.0630   0.00957   0.00322  -0.0928   0.8955   0.0171
  -4.000  -0.0353   0.00926   0.00290  -0.0927   0.8871   0.0228
  -3.750  -0.0078   0.00900   0.00268  -0.0925   0.8788   0.0339
  -3.250   0.0474   0.00870   0.00232  -0.0922   0.8618   0.0493
  -3.000   0.0750   0.00854   0.00217  -0.0920   0.8534   0.0595
  -2.750   0.1025   0.00841   0.00203  -0.0919   0.8442   0.0688
  -2.500   0.1300   0.00827   0.00189  -0.0917   0.8351   0.0804
  -2.250   0.1575   0.00815   0.00176  -0.0915   0.8258   0.0938
  -2.000   0.1850   0.00803   0.00165  -0.0913   0.8158   0.1085
  -1.750   0.2124   0.00791   0.00155  -0.0911   0.8057   0.1296
  -1.500   0.2397   0.00778   0.00147  -0.0909   0.7950   0.1597
  -1.000   0.2941   0.00749   0.00134  -0.0905   0.7711   0.2430
  -0.750   0.3211   0.00730   0.00130  -0.0904   0.7589   0.3091
  -0.500   0.3480   0.00711   0.00128  -0.0902   0.7457   0.3817
  -0.250   0.3747   0.00694   0.00128  -0.0899   0.7307   0.4607
   0.000   0.4012   0.00681   0.00129  -0.0896   0.7149   0.5324
   0.250   0.4273   0.00665   0.00132  -0.0892   0.6988   0.6142
   0.500   0.4526   0.00651   0.00136  -0.0885   0.6819   0.6991
   0.750   0.4766   0.00636   0.00142  -0.0874   0.6634   0.7865
   1.000   0.4969   0.00621   0.00147  -0.0853   0.6435   0.8870
   1.250   0.5317   0.00621   0.00144  -0.0865   0.6193   1.0000
   1.500   0.5577   0.00638   0.00149  -0.0861   0.5943   1.0000
   2.000   0.6091   0.00681   0.00162  -0.0851   0.5344   1.0000
   2.250   0.6345   0.00706   0.00172  -0.0845   0.5015   1.0000
   2.500   0.6597   0.00734   0.00184  -0.0840   0.4673   1.0000
   2.750   0.6851   0.00763   0.00197  -0.0835   0.4353   1.0000
   3.000   0.7105   0.00792   0.00212  -0.0831   0.4035   1.0000
   3.250   0.7355   0.00825   0.00228  -0.0826   0.3686   1.0000
   3.500   0.7608   0.00856   0.00247  -0.0821   0.3391   1.0000
   3.750   0.7859   0.00889   0.00266  -0.0816   0.3092   1.0000
   4.000   0.8109   0.00923   0.00287  -0.0812   0.2798   1.0000
   4.250   0.8362   0.00956   0.00309  -0.0807   0.2553   1.0000
   4.500   0.8611   0.00991   0.00333  -0.0803   0.2302   1.0000
   4.750   0.8861   0.01025   0.00357  -0.0798   0.2081   1.0000
   5.000   0.9111   0.01059   0.00383  -0.0793   0.1877   1.0000
   5.250   0.9358   0.01095   0.00410  -0.0789   0.1675   1.0000
   5.500   0.9604   0.01132   0.00440  -0.0784   0.1501   1.0000
   5.750   0.9851   0.01168   0.00469  -0.0779   0.1356   1.0000
   6.250   1.0344   0.01238   0.00531  -0.0769   0.1113   1.0000
   6.500   1.0590   0.01272   0.00565  -0.0763   0.1022   1.0000
   6.750   1.0832   0.01310   0.00600  -0.0758   0.0925   1.0000
   7.000   1.1071   0.01349   0.00637  -0.0752   0.0838   1.0000
   7.250   1.1312   0.01386   0.00674  -0.0746   0.0759   1.0000
   7.500   1.1547   0.01428   0.00716  -0.0740   0.0680   1.0000
   7.750   1.1780   0.01471   0.00758  -0.0733   0.0608   1.0000
   8.000   1.2011   0.01515   0.00802  -0.0726   0.0544   1.0000
   8.250   1.2233   0.01567   0.00851  -0.0718   0.0471   1.0000
   8.500   1.2457   0.01614   0.00899  -0.0710   0.0416   1.0000
   8.750   1.2674   0.01668   0.00954  -0.0701   0.0365   1.0000
   9.000   1.2891   0.01718   0.01008  -0.0693   0.0327   1.0000
   9.250   1.3097   0.01780   0.01070  -0.0682   0.0289   1.0000
   9.500   1.3310   0.01830   0.01126  -0.0673   0.0268   1.0000
   9.750   1.3512   0.01888   0.01189  -0.0663   0.0242   1.0000
  10.000   1.3699   0.01959   0.01261  -0.0650   0.0214   1.0000
  10.250   1.3896   0.02014   0.01326  -0.0639   0.0197   1.0000
  10.500   1.4078   0.02081   0.01397  -0.0626   0.0177   1.0000
  10.750   1.4240   0.02162   0.01482  -0.0610   0.0158   1.0000
  11.000   1.4406   0.02229   0.01558  -0.0595   0.0149   1.0000
  11.250   1.4547   0.02302   0.01638  -0.0575   0.0137   1.0000
  11.500   1.4670   0.02383   0.01726  -0.0554   0.0127   1.0000
  11.750   1.4768   0.02482   0.01831  -0.0530   0.0116   1.0000
  12.000   1.4874   0.02574   0.01934  -0.0508   0.0110   1.0000
  12.250   1.4976   0.02670   0.02040  -0.0487   0.0104   1.0000
  12.500   1.5069   0.02775   0.02155  -0.0467   0.0097   1.0000
  12.750   1.5147   0.02894   0.02283  -0.0447   0.0092   1.0000
  13.000   1.5206   0.03032   0.02430  -0.0426   0.0087   1.0000
  13.250   1.5236   0.03200   0.02609  -0.0406   0.0083   1.0000
  13.500   1.5265   0.03376   0.02796  -0.0388   0.0080   1.0000
  13.750   1.5304   0.03551   0.02984  -0.0372   0.0078   1.0000
  14.000   1.5330   0.03746   0.03193  -0.0359   0.0075   1.0000
  14.250   1.5350   0.03958   0.03418  -0.0348   0.0073   1.0000
  14.500   1.5345   0.04206   0.03679  -0.0339   0.0070   1.0000
  14.750   1.5341   0.04466   0.03954  -0.0334   0.0068   1.0000
  15.000   1.5323   0.04758   0.04259  -0.0331   0.0066   1.0000
  15.250   1.5272   0.05106   0.04621  -0.0333   0.0064   1.0000
  15.500   1.5217   0.05482   0.05010  -0.0338   0.0063   1.0000
  15.750   1.5127   0.05932   0.05475  -0.0350   0.0062   1.0000
  16.000   1.5020   0.06436   0.05993  -0.0367   0.0060   1.0000
  16.250   1.4886   0.07021   0.06596  -0.0391   0.0060   1.0000
  16.500   1.4727   0.07688   0.07279  -0.0422   0.0059   1.0000
  16.750   1.4549   0.08431   0.08039  -0.0460   0.0058   1.0000
  17.000   1.4351   0.09253   0.08879  -0.0504   0.0058   1.0000
  17.250   1.4137   0.10139   0.09782  -0.0553   0.0058   1.0000
  17.500   1.3923   0.11054   0.10713  -0.0604   0.0059   1.0000
  17.750   1.3694   0.12023   0.11698  -0.0660   0.0059   1.0000
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