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S4158 (s4158-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 100,000
Max Cl/Cd: 57.12 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4158-il-100000.txt
Download as CSV file: xf-s4158-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4471   0.10795   0.10385  -0.0284   1.0000   0.0881
  -8.000  -0.4732   0.10699   0.10297  -0.0276   1.0000   0.0884
  -7.750  -0.4943   0.10509   0.10113  -0.0287   1.0000   0.0885
  -7.500  -0.4892   0.10049   0.09658  -0.0250   1.0000   0.0898
  -7.250  -0.4689   0.09729   0.09336  -0.0202   1.0000   0.0929
  -7.000  -0.4744   0.09496   0.09107  -0.0196   0.9989   0.0951
  -6.750  -0.4711   0.09132   0.08743  -0.0237   0.9955   0.0985
  -6.500  -0.4855   0.08632   0.08212  -0.0407   0.9892   0.1030
  -6.250  -0.4676   0.08175   0.07778  -0.0358   0.9875   0.1050
  -6.000  -0.4509   0.07894   0.07498  -0.0351   0.9847   0.1093
  -5.750  -0.4500   0.07382   0.06951  -0.0450   0.9797   0.1181
  -5.500  -0.4348   0.07098   0.06687  -0.0415   0.9769   0.1214
  -5.250  -0.4184   0.06665   0.06221  -0.0480   0.9727   0.1332
  -5.000  -0.4031   0.06452   0.06023  -0.0455   0.9694   0.1407
  -4.750  -0.3913   0.06120   0.05678  -0.0470   0.9653   0.1513
  -4.500  -0.3714   0.05797   0.05340  -0.0494   0.9612   0.1651
  -4.250  -0.3492   0.05514   0.05045  -0.0511   0.9571   0.1803
  -4.000  -0.3350   0.05276   0.04798  -0.0508   0.9525   0.1955
  -3.750  -0.2772   0.03893   0.03182  -0.0570   0.9501   0.0718
  -3.500  -0.2418   0.03545   0.02763  -0.0583   0.9463   0.0650
  -3.250  -0.2143   0.03367   0.02514  -0.0576   0.9417   0.0623
  -3.000  -0.1872   0.03191   0.02308  -0.0576   0.9369   0.0633
  -2.750  -0.1508   0.03104   0.02209  -0.0594   0.9323   0.0697
  -2.500  -0.1270   0.03019   0.02099  -0.0586   0.9267   0.0729
  -2.250  -0.0965   0.02903   0.01976  -0.0589   0.9215   0.0783
  -2.000  -0.0586   0.02830   0.01910  -0.0606   0.9169   0.0960
  -1.750  -0.0418   0.02758   0.01850  -0.0588   0.9100   0.1305
  -1.500   0.0321   0.02398   0.01835  -0.0668   0.9081   0.9998
  -1.250   0.0703   0.02457   0.01846  -0.0690   0.9023   1.0000
  -1.000   0.0878   0.02490   0.01852  -0.0676   0.8942   1.0000
  -0.750   0.1255   0.02548   0.01880  -0.0697   0.8881   1.0000
  -0.500   0.1440   0.02584   0.01897  -0.0685   0.8795   1.0000
  -0.250   0.1756   0.02636   0.01926  -0.0694   0.8723   1.0000
   0.000   0.2022   0.02678   0.01952  -0.0696   0.8642   1.0000
   0.250   0.2268   0.02726   0.01985  -0.0693   0.8557   1.0000
   0.500   0.2624   0.02769   0.02013  -0.0709   0.8486   1.0000
   0.750   0.2817   0.02814   0.02047  -0.0697   0.8389   1.0000
   1.000   0.3244   0.02853   0.02075  -0.0723   0.8331   1.0000
   1.250   0.3394   0.02897   0.02112  -0.0705   0.8223   1.0000
   1.500   0.3704   0.02938   0.02145  -0.0711   0.8148   1.0000
   1.750   0.3992   0.02972   0.02173  -0.0714   0.8062   1.0000
   2.000   0.4200   0.03016   0.02213  -0.0705   0.7963   1.0000
   2.250   0.4606   0.03033   0.02226  -0.0724   0.7904   1.0000
   2.500   0.4773   0.03078   0.02269  -0.0708   0.7793   1.0000
   2.750   0.5239   0.03077   0.02268  -0.0735   0.7749   1.0000
   3.000   0.5387   0.03118   0.02308  -0.0715   0.7629   1.0000
   3.250   0.5597   0.03151   0.02342  -0.0705   0.7524   1.0000
   3.500   0.6036   0.03127   0.02321  -0.0725   0.7472   1.0000
   3.750   0.6222   0.03155   0.02354  -0.0710   0.7356   1.0000
   4.000   0.6714   0.03093   0.02298  -0.0734   0.7314   1.0000
   4.250   0.6937   0.03090   0.02300  -0.0722   0.7198   1.0000
   4.500   0.7171   0.03080   0.02298  -0.0710   0.7082   1.0000
   4.750   0.7625   0.02977   0.02205  -0.0723   0.7022   1.0000
   5.000   0.7950   0.02906   0.02142  -0.0719   0.6926   1.0000
   5.250   0.8217   0.02857   0.02102  -0.0709   0.6815   1.0000
   5.500   0.8701   0.02673   0.01935  -0.0717   0.6778   1.0000
   5.750   0.8971   0.02605   0.01878  -0.0705   0.6663   1.0000
   6.000   0.9308   0.02496   0.01781  -0.0699   0.6562   1.0000
   6.250   0.9792   0.02300   0.01604  -0.0707   0.6493   1.0000
   6.500   1.0138   0.02187   0.01503  -0.0702   0.6352   1.0000
   6.750   1.0429   0.02102   0.01428  -0.0689   0.6155   1.0000
   7.000   1.0780   0.01991   0.01321  -0.0683   0.5912   1.0000
   7.250   1.1004   0.01965   0.01295  -0.0664   0.5603   1.0000
   7.500   1.1196   0.01969   0.01295  -0.0643   0.5255   1.0000
   7.750   1.1373   0.01991   0.01305  -0.0620   0.4874   1.0000
   8.000   1.1501   0.02043   0.01342  -0.0593   0.4467   1.0000
   8.250   1.1580   0.02118   0.01401  -0.0560   0.4048   1.0000
   8.500   1.1617   0.02210   0.01474  -0.0524   0.3626   1.0000
   8.750   1.1612   0.02318   0.01562  -0.0483   0.3222   1.0000
   9.000   1.1596   0.02451   0.01670  -0.0444   0.2814   1.0000
   9.250   1.1572   0.02611   0.01800  -0.0408   0.2417   1.0000
   9.500   1.1550   0.02794   0.01952  -0.0375   0.2044   1.0000
   9.750   1.1549   0.02989   0.02116  -0.0346   0.1733   1.0000
  10.000   1.1583   0.03175   0.02283  -0.0321   0.1480   1.0000
  10.250   1.1662   0.03352   0.02451  -0.0301   0.1290   1.0000
  10.500   1.1781   0.03521   0.02614  -0.0285   0.1146   1.0000
  10.750   1.1915   0.03689   0.02776  -0.0271   0.1027   1.0000
  11.000   1.2138   0.03869   0.02943  -0.0263   0.0925   1.0000
  11.250   1.2276   0.04034   0.03124  -0.0250   0.0845   1.0000
  11.500   1.2528   0.04252   0.03351  -0.0246   0.0771   1.0000
  11.750   1.2712   0.04448   0.03552  -0.0238   0.0708   1.0000
  12.000   1.2903   0.04728   0.03859  -0.0230   0.0658   1.0000
  12.250   1.3027   0.04981   0.04140  -0.0217   0.0622   1.0000
  12.500   1.3326   0.05403   0.04558  -0.0227   0.0571   1.0000
  12.750   1.3202   0.05602   0.04796  -0.0193   0.0559   1.0000
  13.000   1.3128   0.05908   0.05142  -0.0168   0.0549   1.0000
  13.250   1.3030   0.06260   0.05531  -0.0146   0.0541   1.0000
  13.500   1.2898   0.06639   0.05944  -0.0126   0.0535   1.0000
  13.750   1.2740   0.07055   0.06392  -0.0111   0.0532   1.0000
  14.000   1.2551   0.07510   0.06878  -0.0101   0.0532   1.0000
  14.250   1.2335   0.08010   0.07406  -0.0098   0.0532   1.0000
  14.500   1.2098   0.08561   0.07983  -0.0102   0.0535   1.0000
  14.750   1.1838   0.09174   0.08620  -0.0115   0.0538   1.0000
  15.000   1.1569   0.09857   0.09324  -0.0139   0.0543   1.0000
  15.250   1.1289   0.10622   0.10108  -0.0174   0.0549   1.0000
  15.500   1.1006   0.11489   0.10990  -0.0220   0.0556   1.0000
  15.750   1.0756   0.12405   0.11916  -0.0272   0.0563   1.0000
  16.000   1.0548   0.13347   0.12864  -0.0322   0.0570   1.0000
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