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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 100,000
Max Cl/Cd: 62.73 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4062-il-100000.txt
Download as CSV file: xf-s4062-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3811   0.10360   0.09936  -0.0301   1.0000   0.0888
  -7.750  -0.4072   0.10366   0.09956  -0.0276   1.0000   0.0892
  -7.500  -0.4308   0.10327   0.09927  -0.0259   1.0000   0.0894
  -7.250  -0.4501   0.10193   0.09800  -0.0283   1.0000   0.0897
  -7.000  -0.4423   0.09720   0.09331  -0.0224   1.0000   0.0911
  -6.750  -0.4372   0.09460   0.09071  -0.0184   1.0000   0.0931
  -6.500  -0.4419   0.09261   0.08876  -0.0168   1.0000   0.0948
  -6.250  -0.4243   0.08845   0.08460  -0.0235   0.9947   0.1000
  -6.000  -0.4055   0.08184   0.07792  -0.0392   0.9865   0.1051
  -5.750  -0.3866   0.07883   0.07492  -0.0372   0.9834   0.1083
  -5.250  -0.3429   0.06977   0.06574  -0.0503   0.9720   0.1220
  -5.000  -0.3214   0.06501   0.06077  -0.0591   0.9649   0.1340
  -4.750  -0.3016   0.06265   0.05847  -0.0575   0.9608   0.1409
  -4.500  -0.2754   0.05836   0.05402  -0.0632   0.9557   0.1518
  -4.250  -0.2190   0.04102   0.03522  -0.0793   0.9520   0.0717
  -4.000  -0.1786   0.03455   0.02753  -0.0830   0.9488   0.0615
  -3.750  -0.1396   0.03127   0.02355  -0.0856   0.9458   0.0613
  -3.500  -0.1071   0.02905   0.02080  -0.0868   0.9419   0.0645
  -3.250  -0.0799   0.02797   0.01960  -0.0871   0.9367   0.0713
  -3.000  -0.0438   0.02639   0.01774  -0.0884   0.9330   0.0800
  -2.750  -0.0052   0.02546   0.01670  -0.0904   0.9295   0.1056
  -2.500   0.0155   0.02490   0.01625  -0.0895   0.9233   0.1371
  -2.250   0.0487   0.02439   0.01587  -0.0909   0.9187   0.1872
  -2.000   0.0848   0.02397   0.01566  -0.0927   0.9148   0.2468
  -1.750   0.1036   0.02371   0.01560  -0.0915   0.9082   0.3007
  -1.500   0.1363   0.02326   0.01559  -0.0927   0.9037   0.4000
  -1.250   0.1655   0.02266   0.01578  -0.0928   0.8994   0.5880
  -1.000   0.1918   0.02192   0.01581  -0.0917   0.8935   1.0000
  -0.750   0.2288   0.02230   0.01584  -0.0937   0.8886   1.0000
  -0.500   0.2532   0.02276   0.01606  -0.0936   0.8820   1.0000
  -0.250   0.2831   0.02316   0.01625  -0.0943   0.8757   1.0000
   0.000   0.3260   0.02351   0.01638  -0.0971   0.8718   1.0000
   0.250   0.3385   0.02403   0.01679  -0.0950   0.8625   1.0000
   0.500   0.3794   0.02433   0.01693  -0.0974   0.8579   1.0000
   0.750   0.3954   0.02487   0.01738  -0.0959   0.8488   1.0000
   1.000   0.4354   0.02512   0.01753  -0.0980   0.8437   1.0000
   1.250   0.4536   0.02566   0.01800  -0.0967   0.8344   1.0000
   1.500   0.4957   0.02577   0.01804  -0.0990   0.8290   1.0000
   1.750   0.5148   0.02626   0.01848  -0.0978   0.8189   1.0000
   2.000   0.5613   0.02616   0.01836  -0.1005   0.8140   1.0000
   2.250   0.5794   0.02662   0.01880  -0.0991   0.8030   1.0000
   2.500   0.6315   0.02620   0.01838  -0.1023   0.7988   1.0000
   2.750   0.6511   0.02654   0.01873  -0.1009   0.7871   1.0000
   3.000   0.6798   0.02661   0.01883  -0.1007   0.7775   1.0000
   3.250   0.7232   0.02598   0.01824  -0.1020   0.7713   1.0000
   3.500   0.7482   0.02606   0.01836  -0.1012   0.7604   1.0000
   3.750   0.7942   0.02507   0.01745  -0.1024   0.7557   1.0000
   4.000   0.8185   0.02504   0.01748  -0.1013   0.7439   1.0000
   4.250   0.8488   0.02465   0.01717  -0.1007   0.7339   1.0000
   4.500   0.8903   0.02354   0.01616  -0.1011   0.7272   1.0000
   4.750   0.9179   0.02314   0.01586  -0.1001   0.7150   1.0000
   5.000   0.9483   0.02252   0.01534  -0.0992   0.7032   1.0000
   5.250   0.9811   0.02170   0.01461  -0.0985   0.6912   1.0000
   5.500   1.0127   0.02090   0.01393  -0.0976   0.6773   1.0000
   5.750   1.0421   0.02020   0.01333  -0.0965   0.6605   1.0000
   6.000   1.0724   0.01944   0.01264  -0.0954   0.6415   1.0000
   6.250   1.0976   0.01899   0.01230  -0.0939   0.6170   1.0000
   6.500   1.1223   0.01861   0.01195  -0.0922   0.5872   1.0000
   6.750   1.1453   0.01841   0.01170  -0.0903   0.5496   1.0000
   7.000   1.1642   0.01856   0.01175  -0.0881   0.5025   1.0000
   7.250   1.1807   0.01908   0.01198  -0.0856   0.4513   1.0000
   7.500   1.1944   0.01995   0.01257  -0.0832   0.4026   1.0000
   7.750   1.2072   0.02101   0.01335  -0.0808   0.3607   1.0000
   8.000   1.2193   0.02213   0.01427  -0.0784   0.3239   1.0000
   8.500   1.2426   0.02450   0.01632  -0.0739   0.2627   1.0000
   8.750   1.2531   0.02574   0.01746  -0.0715   0.2353   1.0000
   9.000   1.2617   0.02701   0.01866  -0.0690   0.2095   1.0000
   9.250   1.2681   0.02835   0.01989  -0.0662   0.1863   1.0000
   9.500   1.2725   0.02970   0.02116  -0.0633   0.1646   1.0000
   9.750   1.2761   0.03116   0.02259  -0.0606   0.1439   1.0000
  10.000   1.2798   0.03272   0.02412  -0.0581   0.1254   1.0000
  10.250   1.2845   0.03455   0.02583  -0.0558   0.1091   1.0000
  10.500   1.2904   0.03655   0.02781  -0.0537   0.0939   1.0000
  10.750   1.2991   0.03876   0.03001  -0.0518   0.0807   1.0000
  11.000   1.3119   0.04106   0.03220  -0.0504   0.0702   1.0000
  11.250   1.3220   0.04309   0.03450  -0.0487   0.0633   1.0000
  11.500   1.3500   0.04614   0.03756  -0.0485   0.0576   1.0000
  11.750   1.3641   0.04878   0.04054  -0.0471   0.0542   1.0000
  12.000   1.3727   0.05112   0.04306  -0.0456   0.0509   1.0000
  12.250   1.3934   0.05537   0.04740  -0.0456   0.0479   1.0000
  12.500   1.3900   0.05852   0.05095  -0.0432   0.0472   1.0000
  12.750   1.3833   0.06208   0.05490  -0.0410   0.0467   1.0000
  13.000   1.3728   0.06595   0.05915  -0.0391   0.0464   1.0000
  13.250   1.3586   0.07017   0.06371  -0.0376   0.0462   1.0000
  13.500   1.3420   0.07473   0.06859  -0.0366   0.0462   1.0000
  13.750   1.3227   0.07974   0.07390  -0.0362   0.0463   1.0000
  14.000   1.3016   0.08520   0.07963  -0.0366   0.0464   1.0000
  14.250   1.2790   0.09117   0.08585  -0.0378   0.0466   1.0000
  14.500   1.2553   0.09770   0.09260  -0.0399   0.0469   1.0000
  14.750   1.2315   0.10479   0.09989  -0.0429   0.0472   1.0000
  15.000   1.2075   0.11255   0.10782  -0.0468   0.0476   1.0000
  15.250   1.1849   0.12098   0.11638  -0.0514   0.0480   1.0000
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