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S4158 (s4158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.33 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4158-il-1000000-n5.txt
Download as CSV file: xf-s4158-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4158                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5155   0.04256   0.04003  -0.0718   0.7901   0.0056
  -8.750  -0.5557   0.02660   0.02303  -0.0731   0.7880   0.0056
  -8.500  -0.5500   0.02196   0.01781  -0.0721   0.7866   0.0058
  -8.250  -0.5315   0.01988   0.01544  -0.0716   0.7852   0.0058
  -8.000  -0.5113   0.01809   0.01338  -0.0711   0.7838   0.0059
  -7.750  -0.4881   0.01692   0.01203  -0.0707   0.7823   0.0060
  -7.500  -0.4639   0.01599   0.01095  -0.0705   0.7809   0.0061
  -7.250  -0.4388   0.01522   0.01006  -0.0703   0.7795   0.0063
  -7.000  -0.4132   0.01456   0.00929  -0.0701   0.7781   0.0064
  -6.750  -0.3874   0.01391   0.00852  -0.0699   0.7767   0.0065
  -6.500  -0.3613   0.01335   0.00786  -0.0697   0.7753   0.0067
  -6.250  -0.3349   0.01281   0.00724  -0.0696   0.7740   0.0069
  -6.000  -0.3081   0.01232   0.00668  -0.0695   0.7727   0.0072
  -5.750  -0.2812   0.01184   0.00612  -0.0695   0.7713   0.0074
  -5.500  -0.2541   0.01143   0.00566  -0.0694   0.7698   0.0077
  -5.250  -0.2270   0.01101   0.00518  -0.0693   0.7683   0.0079
  -5.000  -0.1996   0.01066   0.00478  -0.0693   0.7667   0.0081
  -4.750  -0.1722   0.01035   0.00440  -0.0693   0.7651   0.0082
  -4.500  -0.1446   0.01005   0.00405  -0.0693   0.7635   0.0084
  -4.250  -0.1170   0.00977   0.00373  -0.0692   0.7620   0.0085
  -4.000  -0.0900   0.00935   0.00324  -0.0691   0.7603   0.0089
  -3.750  -0.0622   0.00906   0.00293  -0.0692   0.7586   0.0095
  -3.500  -0.0341   0.00883   0.00270  -0.0692   0.7565   0.0101
  -3.250  -0.0059   0.00863   0.00248  -0.0693   0.7543   0.0108
  -3.000   0.0223   0.00844   0.00227  -0.0694   0.7520   0.0114
  -2.750   0.0505   0.00828   0.00208  -0.0694   0.7497   0.0121
  -2.500   0.0786   0.00810   0.00188  -0.0695   0.7474   0.0142
  -2.250   0.1068   0.00795   0.00174  -0.0696   0.7450   0.0183
  -2.000   0.1350   0.00773   0.00161  -0.0697   0.7419   0.0347
  -1.750   0.1632   0.00756   0.00150  -0.0698   0.7382   0.0508
  -1.500   0.1912   0.00738   0.00139  -0.0699   0.7343   0.0741
  -1.250   0.2191   0.00718   0.00130  -0.0700   0.7307   0.1083
  -1.000   0.2472   0.00699   0.00123  -0.0701   0.7265   0.1479
  -0.750   0.2748   0.00673   0.00116  -0.0702   0.7224   0.2114
  -0.500   0.3018   0.00643   0.00110  -0.0702   0.7184   0.2987
  -0.250   0.3296   0.00622   0.00107  -0.0703   0.7138   0.3616
   0.000   0.3567   0.00597   0.00104  -0.0704   0.7084   0.4450
   0.250   0.3837   0.00574   0.00102  -0.0703   0.7029   0.5239
   0.500   0.4105   0.00551   0.00103  -0.0702   0.6961   0.6073
   0.750   0.4365   0.00529   0.00103  -0.0699   0.6886   0.6927
   1.000   0.4608   0.00502   0.00106  -0.0691   0.6796   0.7946
   1.250   0.4846   0.00476   0.00111  -0.0680   0.6696   0.9070
   1.500   0.5320   0.00477   0.00114  -0.0722   0.6570   0.9656
   1.750   0.5689   0.00489   0.00117  -0.0743   0.6385   0.9798
   2.000   0.6025   0.00507   0.00123  -0.0757   0.6144   0.9884
   2.500   0.6711   0.00544   0.00139  -0.0789   0.5682   0.9986
   2.750   0.7012   0.00564   0.00150  -0.0796   0.5460   1.0000
   3.000   0.7263   0.00585   0.00161  -0.0792   0.5243   1.0000
   3.250   0.7509   0.00608   0.00174  -0.0788   0.5016   1.0000
   3.500   0.7756   0.00631   0.00188  -0.0783   0.4803   1.0000
   3.750   0.7998   0.00657   0.00204  -0.0778   0.4569   1.0000
   4.000   0.8242   0.00680   0.00220  -0.0773   0.4367   1.0000
   4.250   0.8479   0.00708   0.00238  -0.0767   0.4143   1.0000
   4.500   0.8705   0.00744   0.00260  -0.0759   0.3836   1.0000
   4.750   0.8912   0.00791   0.00288  -0.0749   0.3432   1.0000
   5.000   0.9125   0.00831   0.00313  -0.0739   0.3102   1.0000
   5.250   0.9321   0.00882   0.00344  -0.0727   0.2698   1.0000
   5.500   0.9522   0.00928   0.00374  -0.0716   0.2373   1.0000
   5.750   0.9725   0.00970   0.00404  -0.0704   0.2111   1.0000
   6.000   0.9924   0.01014   0.00435  -0.0693   0.1868   1.0000
   6.250   1.0134   0.01049   0.00464  -0.0683   0.1691   1.0000
   6.500   1.0332   0.01091   0.00495  -0.0671   0.1496   1.0000
   6.750   1.0522   0.01134   0.00530  -0.0658   0.1300   1.0000
   7.000   1.0712   0.01176   0.00564  -0.0645   0.1130   1.0000
   7.250   1.0880   0.01228   0.00605  -0.0629   0.0936   1.0000
   7.500   1.1050   0.01274   0.00644  -0.0613   0.0784   1.0000
   7.750   1.1196   0.01319   0.00684  -0.0592   0.0673   1.0000
   8.000   1.1331   0.01365   0.00728  -0.0570   0.0587   1.0000
   8.250   1.1479   0.01412   0.00772  -0.0551   0.0511   1.0000
   8.500   1.1631   0.01462   0.00820  -0.0534   0.0446   1.0000
   8.750   1.1784   0.01515   0.00871  -0.0518   0.0387   1.0000
   9.000   1.1947   0.01567   0.00922  -0.0503   0.0341   1.0000
   9.250   1.2107   0.01621   0.00975  -0.0489   0.0307   1.0000
   9.500   1.2267   0.01677   0.01033  -0.0475   0.0276   1.0000
   9.750   1.2436   0.01728   0.01087  -0.0463   0.0258   1.0000
  10.000   1.2596   0.01787   0.01147  -0.0450   0.0236   1.0000
  10.250   1.2744   0.01854   0.01214  -0.0436   0.0206   1.0000
  10.500   1.2906   0.01913   0.01277  -0.0424   0.0195   1.0000
  10.750   1.3058   0.01979   0.01345  -0.0411   0.0178   1.0000
  11.000   1.3198   0.02054   0.01421  -0.0397   0.0160   1.0000
  11.250   1.3345   0.02126   0.01497  -0.0385   0.0149   1.0000
  11.500   1.3490   0.02200   0.01574  -0.0372   0.0138   1.0000
  11.750   1.3625   0.02281   0.01658  -0.0359   0.0126   1.0000
  12.000   1.3747   0.02373   0.01752  -0.0346   0.0114   1.0000
  12.250   1.3879   0.02459   0.01842  -0.0333   0.0105   1.0000
  12.500   1.4003   0.02550   0.01939  -0.0321   0.0099   1.0000
  12.750   1.4116   0.02653   0.02045  -0.0308   0.0088   1.0000
  13.000   1.4218   0.02764   0.02160  -0.0294   0.0081   1.0000
  13.250   1.4328   0.02871   0.02272  -0.0282   0.0076   1.0000
  13.500   1.4428   0.02987   0.02394  -0.0270   0.0070   1.0000
  13.750   1.4529   0.03104   0.02518  -0.0258   0.0068   1.0000
  14.000   1.4615   0.03237   0.02657  -0.0246   0.0066   1.0000
  14.250   1.4693   0.03377   0.02801  -0.0234   0.0061   1.0000
  14.500   1.4760   0.03532   0.02962  -0.0223   0.0057   1.0000
  14.750   1.4817   0.03702   0.03140  -0.0212   0.0054   1.0000
  15.000   1.4886   0.03865   0.03311  -0.0203   0.0053   1.0000
  15.250   1.4953   0.04034   0.03489  -0.0194   0.0051   1.0000
  15.500   1.5000   0.04229   0.03693  -0.0186   0.0050   1.0000
  15.750   1.5054   0.04423   0.03894  -0.0180   0.0048   1.0000
  16.000   1.5092   0.04636   0.04117  -0.0174   0.0047   1.0000
  16.250   1.5125   0.04865   0.04354  -0.0170   0.0045   1.0000
  16.500   1.5134   0.05127   0.04625  -0.0166   0.0044   1.0000
  16.750   1.5157   0.05382   0.04888  -0.0164   0.0042   1.0000
  17.000   1.5165   0.05661   0.05176  -0.0164   0.0041   1.0000
  17.250   1.5145   0.05982   0.05506  -0.0166   0.0040   1.0000
  17.500   1.5115   0.06329   0.05863  -0.0169   0.0038   1.0000
  17.750   1.5078   0.06698   0.06244  -0.0175   0.0038   1.0000
  18.000   1.5005   0.07128   0.06686  -0.0184   0.0037   1.0000
  18.250   1.4926   0.07579   0.07150  -0.0195   0.0035   1.0000
  18.500   1.4858   0.08031   0.07613  -0.0208   0.0035   1.0000
  18.750   1.4778   0.08515   0.08109  -0.0225   0.0035   1.0000
  19.000   1.4695   0.09015   0.08621  -0.0243   0.0035   1.0000
  19.250   1.4612   0.09526   0.09144  -0.0263   0.0034   1.0000
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