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S4158 (s4158-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 200,000
Max Cl/Cd: 84.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4158-il-200000.txt
Download as CSV file: xf-s4158-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2299   0.08859   0.08516  -0.0851   0.9598   0.0487
  -9.000  -0.2278   0.08479   0.08137  -0.0903   0.9548   0.0489
  -8.750  -0.2285   0.08059   0.07718  -0.0960   0.9487   0.0490
  -8.500  -0.2130   0.07656   0.07316  -0.0903   0.9489   0.0507
  -8.250  -0.2022   0.07403   0.07063  -0.0907   0.9461   0.0518
  -8.000  -0.1971   0.07144   0.06805  -0.0919   0.9419   0.0535
  -7.750  -0.1985   0.06851   0.06514  -0.0943   0.9364   0.0545
  -7.500  -0.2000   0.06519   0.06179  -0.0975   0.9316   0.0559
  -7.250  -0.2009   0.06126   0.05780  -0.1017   0.9262   0.0581
  -7.000  -0.2124   0.05793   0.05391  -0.1068   0.9189   0.0614
  -6.750  -0.2103   0.05232   0.04831  -0.1072   0.9154   0.0626
  -6.500  -0.1978   0.04991   0.04596  -0.1065   0.9117   0.0639
  -6.250  -0.1854   0.04788   0.04390  -0.1059   0.9082   0.0657
  -6.000  -0.1722   0.04555   0.04142  -0.1056   0.9050   0.0692
  -5.750  -0.1711   0.04281   0.03813  -0.1044   0.8994   0.0763
  -5.500  -0.1566   0.04052   0.03590  -0.1036   0.8955   0.0782
  -5.250  -0.1455   0.03183   0.02570  -0.0992   0.8913   0.0381
  -5.000  -0.1263   0.02942   0.02292  -0.0980   0.8887   0.0382
  -4.750  -0.1153   0.02786   0.02109  -0.0956   0.8829   0.0384
  -4.500  -0.0920   0.02670   0.01968  -0.0946   0.8794   0.0377
  -4.250  -0.0667   0.02460   0.01728  -0.0939   0.8770   0.0373
  -3.750  -0.0257   0.02249   0.01480  -0.0911   0.8684   0.0382
  -3.500  -0.0016   0.02116   0.01344  -0.0904   0.8651   0.0400
  -3.250   0.0258   0.02042   0.01270  -0.0900   0.8626   0.0436
  -3.000   0.0465   0.02018   0.01238  -0.0887   0.8581   0.0496
  -2.750   0.0653   0.01967   0.01191  -0.0871   0.8525   0.0608
  -2.500   0.0894   0.01871   0.01119  -0.0862   0.8494   0.1144
  -2.250   0.1146   0.01782   0.01091  -0.0858   0.8472   0.2509
  -2.000   0.1212   0.01732   0.01126  -0.0828   0.8390   0.4583
  -1.750   0.1384   0.01656   0.01128  -0.0801   0.8355   0.6721
  -1.500   0.1968   0.01597   0.01125  -0.0847   0.8350   0.9089
  -1.250   0.2887   0.01579   0.01088  -0.0970   0.8357   0.9851
  -1.000   0.3449   0.01560   0.01051  -0.1025   0.8343   1.0000
  -0.750   0.3605   0.01586   0.01068  -0.1006   0.8276   1.0000
  -0.500   0.3805   0.01591   0.01062  -0.0991   0.8221   1.0000
  -0.250   0.4055   0.01579   0.01039  -0.0980   0.8191   1.0000
   0.000   0.4212   0.01612   0.01066  -0.0962   0.8107   1.0000
   0.250   0.4457   0.01602   0.01048  -0.0952   0.8066   1.0000
   0.500   0.4723   0.01584   0.01021  -0.0943   0.8041   1.0000
   0.750   0.4887   0.01621   0.01055  -0.0926   0.7949   1.0000
   1.000   0.5152   0.01604   0.01032  -0.0918   0.7916   1.0000
   1.250   0.5425   0.01582   0.01004  -0.0910   0.7892   1.0000
   1.500   0.5601   0.01616   0.01037  -0.0896   0.7796   1.0000
   1.750   0.5877   0.01591   0.01008  -0.0889   0.7766   1.0000
   2.000   0.6089   0.01605   0.01022  -0.0877   0.7694   1.0000
   2.250   0.6348   0.01588   0.01003  -0.0869   0.7644   1.0000
   2.500   0.6633   0.01553   0.00966  -0.0863   0.7614   1.0000
   2.750   0.6846   0.01563   0.00978  -0.0851   0.7527   1.0000
   3.000   0.7129   0.01524   0.00940  -0.0845   0.7485   1.0000
   3.250   0.7379   0.01502   0.00919  -0.0836   0.7413   1.0000
   3.500   0.7657   0.01452   0.00869  -0.0828   0.7348   1.0000
   3.750   0.7914   0.01419   0.00840  -0.0819   0.7266   1.0000
   4.000   0.8198   0.01369   0.00790  -0.0812   0.7200   1.0000
   4.250   0.8444   0.01348   0.00774  -0.0803   0.7101   1.0000
   4.500   0.8731   0.01303   0.00730  -0.0798   0.7030   1.0000
   4.750   0.8986   0.01279   0.00712  -0.0790   0.6919   1.0000
   5.000   0.9238   0.01261   0.00698  -0.0782   0.6794   1.0000
   5.250   0.9496   0.01242   0.00682  -0.0774   0.6658   1.0000
   5.500   0.9757   0.01225   0.00665  -0.0766   0.6503   1.0000
   5.750   1.0004   0.01218   0.00659  -0.0757   0.6300   1.0000
   6.000   1.0243   0.01219   0.00651  -0.0746   0.6046   1.0000
   6.250   1.0461   0.01237   0.00661  -0.0733   0.5756   1.0000
   6.500   1.0663   0.01267   0.00682  -0.0718   0.5442   1.0000
   6.750   1.0849   0.01307   0.00713  -0.0702   0.5104   1.0000
   7.000   1.1015   0.01358   0.00749  -0.0683   0.4758   1.0000
   7.250   1.1161   0.01417   0.00795  -0.0661   0.4389   1.0000
   7.500   1.1282   0.01486   0.00847  -0.0636   0.4026   1.0000
   7.750   1.1380   0.01561   0.00908  -0.0609   0.3643   1.0000
   8.000   1.1450   0.01644   0.00976  -0.0578   0.3260   1.0000
   8.250   1.1477   0.01733   0.01049  -0.0541   0.2901   1.0000
   8.500   1.1502   0.01837   0.01135  -0.0506   0.2546   1.0000
   8.750   1.1535   0.01955   0.01233  -0.0476   0.2198   1.0000
   9.000   1.1572   0.02082   0.01342  -0.0448   0.1870   1.0000
   9.250   1.1615   0.02216   0.01459  -0.0422   0.1535   1.0000
   9.500   1.1646   0.02368   0.01591  -0.0396   0.1238   1.0000
   9.750   1.1685   0.02522   0.01730  -0.0372   0.1032   1.0000
  10.000   1.1738   0.02673   0.01877  -0.0350   0.0895   1.0000
  10.250   1.1780   0.02836   0.02033  -0.0328   0.0801   1.0000
  10.500   1.1868   0.02970   0.02171  -0.0310   0.0722   1.0000
  10.750   1.1930   0.03132   0.02335  -0.0291   0.0660   1.0000
  11.000   1.2018   0.03272   0.02481  -0.0276   0.0607   1.0000
  11.250   1.2079   0.03456   0.02662  -0.0258   0.0560   1.0000
  11.500   1.2186   0.03589   0.02808  -0.0244   0.0518   1.0000
  11.750   1.2266   0.03753   0.02972  -0.0230   0.0480   1.0000
  12.000   1.2375   0.03932   0.03161  -0.0216   0.0445   1.0000
  12.250   1.2471   0.04084   0.03327  -0.0204   0.0414   1.0000
  12.500   1.2571   0.04250   0.03498  -0.0192   0.0389   1.0000
  12.750   1.2743   0.04483   0.03733  -0.0182   0.0359   1.0000
  13.000   1.2808   0.04659   0.03932  -0.0169   0.0342   1.0000
  13.250   1.2870   0.04854   0.04144  -0.0158   0.0322   1.0000
  13.500   1.2927   0.05061   0.04363  -0.0147   0.0305   1.0000
  13.750   1.2999   0.05277   0.04586  -0.0139   0.0292   1.0000
  14.250   1.3082   0.05989   0.05348  -0.0118   0.0272   1.0000
  14.500   1.3029   0.06317   0.05703  -0.0109   0.0269   1.0000
  14.750   1.2945   0.06684   0.06097  -0.0103   0.0264   1.0000
  15.000   1.2844   0.07078   0.06517  -0.0101   0.0259   1.0000
  15.250   1.2721   0.07519   0.06984  -0.0103   0.0255   1.0000
  15.500   1.2572   0.08030   0.07520  -0.0110   0.0253   1.0000
  15.750   1.2429   0.08536   0.08048  -0.0123   0.0248   1.0000
  16.000   1.2220   0.09206   0.08745  -0.0144   0.0250   1.0000
  16.250   1.2048   0.09829   0.09389  -0.0171   0.0246   1.0000
  16.500   1.1777   0.10703   0.10288  -0.0213   0.0252   1.0000
  16.750   1.1547   0.11544   0.11150  -0.0260   0.0251   1.0000
  17.000   1.1284   0.12527   0.12152  -0.0320   0.0256   1.0000
  17.250   1.0974   0.13709   0.13352  -0.0394   0.0264   1.0000
  17.500   1.0676   0.14968   0.14620  -0.0473   0.0271   1.0000
  17.750   1.0395   0.16404   0.16068  -0.0564   0.0282   1.0000
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