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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 500,000
Max Cl/Cd: 98.48 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4083-il-500000-n5.txt
Download as CSV file: xf-s4083-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3838   0.08797   0.08579  -0.0183   1.0000   0.0103
  -7.500  -0.3855   0.08511   0.08297  -0.0184   1.0000   0.0103
  -7.250  -0.3904   0.08236   0.08027  -0.0180   1.0000   0.0103
  -7.000  -0.3888   0.07906   0.07700  -0.0192   1.0000   0.0103
  -6.750  -0.3854   0.07552   0.07349  -0.0212   1.0000   0.0103
  -6.500  -0.3635   0.07000   0.06796  -0.0288   0.9977   0.0103
  -6.250  -0.3359   0.06388   0.06179  -0.0380   0.9943   0.0103
  -5.250  -0.2223   0.03089   0.02795  -0.0709   0.9665   0.0065
  -5.000  -0.1934   0.02218   0.01845  -0.0742   0.9584   0.0066
  -4.750  -0.1629   0.01808   0.01369  -0.0757   0.9505   0.0068
  -4.500  -0.1320   0.01530   0.01042  -0.0769   0.9408   0.0072
  -4.250  -0.0935   0.01382   0.00866  -0.0793   0.9294   0.0075
  -4.000  -0.0429   0.01277   0.00741  -0.0844   0.9146   0.0081
  -3.750   0.0159   0.01178   0.00613  -0.0912   0.8838   0.0090
  -3.500   0.0559   0.01096   0.00493  -0.0936   0.8293   0.0091
  -3.250   0.0812   0.01056   0.00420  -0.0928   0.7757   0.0091
  -3.000   0.1043   0.01026   0.00362  -0.0915   0.7303   0.0092
  -2.750   0.1276   0.01002   0.00312  -0.0904   0.6907   0.0095
  -2.500   0.1517   0.00983   0.00273  -0.0894   0.6569   0.0097
  -2.250   0.1765   0.00970   0.00239  -0.0886   0.6275   0.0101
  -2.000   0.2017   0.00955   0.00207  -0.0878   0.6026   0.0111
  -1.750   0.2273   0.00944   0.00184  -0.0872   0.5806   0.0141
  -1.500   0.2531   0.00931   0.00166  -0.0866   0.5616   0.0278
  -1.250   0.2787   0.00911   0.00155  -0.0862   0.5436   0.0747
  -1.000   0.3044   0.00892   0.00148  -0.0857   0.5278   0.1378
  -0.750   0.3298   0.00866   0.00144  -0.0853   0.5134   0.2388
  -0.500   0.3551   0.00842   0.00143  -0.0849   0.4997   0.3414
  -0.250   0.3804   0.00821   0.00145  -0.0844   0.4872   0.4466
   0.000   0.4052   0.00800   0.00149  -0.0838   0.4763   0.5566
   0.250   0.4297   0.00785   0.00153  -0.0830   0.4656   0.6514
   0.500   0.4538   0.00769   0.00155  -0.0821   0.4551   0.7296
   1.000   0.5258   0.00737   0.00159  -0.0853   0.4345   1.0000
   1.250   0.5521   0.00749   0.00162  -0.0849   0.4249   1.0000
   1.500   0.5785   0.00760   0.00166  -0.0845   0.4157   1.0000
   1.750   0.6048   0.00772   0.00171  -0.0840   0.4062   1.0000
   2.000   0.6310   0.00785   0.00178  -0.0836   0.3966   1.0000
   2.250   0.6574   0.00797   0.00184  -0.0832   0.3880   1.0000
   2.500   0.6835   0.00811   0.00192  -0.0828   0.3800   1.0000
   2.750   0.7100   0.00823   0.00201  -0.0824   0.3720   1.0000
   3.000   0.7362   0.00837   0.00212  -0.0820   0.3641   1.0000
   3.250   0.7624   0.00850   0.00223  -0.0816   0.3560   1.0000
   3.500   0.7886   0.00864   0.00234  -0.0812   0.3480   1.0000
   3.750   0.8146   0.00880   0.00247  -0.0807   0.3391   1.0000
   4.000   0.8407   0.00895   0.00262  -0.0803   0.3296   1.0000
   4.250   0.8666   0.00912   0.00276  -0.0799   0.3206   1.0000
   4.500   0.8924   0.00929   0.00291  -0.0795   0.3113   1.0000
   4.750   0.9184   0.00945   0.00308  -0.0791   0.3026   1.0000
   5.000   0.9440   0.00965   0.00328  -0.0786   0.2915   1.0000
   5.250   0.9694   0.00986   0.00347  -0.0781   0.2792   1.0000
   5.500   0.9946   0.01010   0.00368  -0.0776   0.2669   1.0000
   6.000   1.0442   0.01064   0.00415  -0.0765   0.2350   1.0000
   6.250   1.0674   0.01108   0.00448  -0.0757   0.2042   1.0000
   6.500   1.0907   0.01152   0.00482  -0.0750   0.1804   1.0000
   6.750   1.1119   0.01219   0.00528  -0.0740   0.1430   1.0000
   7.000   1.1324   0.01293   0.00582  -0.0729   0.1068   1.0000
   7.250   1.1541   0.01353   0.00633  -0.0720   0.0835   1.0000
   7.500   1.1752   0.01417   0.00688  -0.0709   0.0621   1.0000
   7.750   1.1942   0.01505   0.00759  -0.0696   0.0351   1.0000
   8.000   1.2115   0.01608   0.00848  -0.0680   0.0118   1.0000
   8.250   1.2316   0.01677   0.00918  -0.0668   0.0068   1.0000
   8.500   1.2525   0.01737   0.00984  -0.0657   0.0055   1.0000
   8.750   1.2733   0.01794   0.01052  -0.0646   0.0052   1.0000
   9.000   1.2935   0.01856   0.01123  -0.0634   0.0048   1.0000
   9.250   1.3125   0.01926   0.01203  -0.0621   0.0044   1.0000
   9.500   1.3308   0.01999   0.01287  -0.0606   0.0042   1.0000
   9.750   1.3476   0.02084   0.01382  -0.0590   0.0040   1.0000
  10.000   1.3623   0.02181   0.01492  -0.0571   0.0038   1.0000
  10.250   1.3752   0.02286   0.01609  -0.0550   0.0037   1.0000
  10.500   1.3826   0.02425   0.01764  -0.0522   0.0035   1.0000
  10.750   1.3895   0.02543   0.01896  -0.0492   0.0035   1.0000
  11.000   1.3944   0.02655   0.02019  -0.0460   0.0035   1.0000
  11.250   1.3971   0.02782   0.02159  -0.0427   0.0034   1.0000
  11.500   1.3983   0.02924   0.02312  -0.0396   0.0034   1.0000
  11.750   1.3974   0.03089   0.02490  -0.0366   0.0034   1.0000
  12.000   1.3952   0.03279   0.02694  -0.0342   0.0034   1.0000
  12.250   1.3914   0.03506   0.02935  -0.0323   0.0034   1.0000
  12.500   1.3872   0.03768   0.03210  -0.0311   0.0033   1.0000
  12.750   1.3827   0.04068   0.03525  -0.0306   0.0033   1.0000
  13.000   1.3773   0.04417   0.03889  -0.0309   0.0033   1.0000
  13.250   1.3727   0.04786   0.04271  -0.0316   0.0033   1.0000
  13.500   1.3682   0.05175   0.04674  -0.0327   0.0032   1.0000
  13.750   1.3594   0.05639   0.05153  -0.0342   0.0032   1.0000
  14.000   1.3531   0.06082   0.05610  -0.0357   0.0032   1.0000
  14.250   1.3451   0.06558   0.06099  -0.0375   0.0032   1.0000
  14.500   1.3361   0.07058   0.06612  -0.0394   0.0031   1.0000
  14.750   1.3287   0.07548   0.07114  -0.0414   0.0031   1.0000
  15.000   1.3174   0.08103   0.07683  -0.0436   0.0030   1.0000
  15.250   1.3069   0.08666   0.08259  -0.0461   0.0030   1.0000
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