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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.27 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4083-il-1000000.txt
Download as CSV file: xf-s4083-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3896   0.08516   0.08365  -0.0150   1.0000   0.0088
  -7.250  -0.3944   0.08263   0.08115  -0.0144   1.0000   0.0091
  -7.000  -0.3998   0.07981   0.07837  -0.0142   1.0000   0.0093
  -6.750  -0.3979   0.07620   0.07478  -0.0162   1.0000   0.0095
  -6.500  -0.3899   0.07217   0.07076  -0.0200   0.9999   0.0099
  -6.250  -0.3577   0.06583   0.06440  -0.0305   0.9978   0.0099
  -6.000  -0.3222   0.05894   0.05744  -0.0418   0.9954   0.0100
  -5.750  -0.2399   0.02929   0.02774  -0.0604   0.9871   0.0103
  -5.500  -0.2154   0.02298   0.02127  -0.0671   0.9830   0.0106
  -5.250  -0.1889   0.01883   0.01695  -0.0712   0.9781   0.0109
  -5.000  -0.1878   0.02993   0.02766  -0.0743   0.9810   0.0110
  -4.750  -0.1551   0.02649   0.02400  -0.0773   0.9768   0.0116
  -4.500  -0.1234   0.02298   0.02020  -0.0793   0.9718   0.0123
  -4.000  -0.0623   0.01350   0.00941  -0.0802   0.9577   0.0102
  -3.750  -0.0283   0.01133   0.00691  -0.0814   0.9495   0.0103
  -3.500   0.0130   0.00974   0.00511  -0.0842   0.9378   0.0106
  -3.250   0.0749   0.00858   0.00377  -0.0917   0.9179   0.0109
  -3.000   0.1217   0.00818   0.00312  -0.0958   0.8613   0.0118
  -2.750   0.1450   0.00799   0.00260  -0.0945   0.7980   0.0118
  -2.500   0.1669   0.00787   0.00220  -0.0929   0.7456   0.0120
  -2.250   0.1901   0.00778   0.00188  -0.0917   0.7024   0.0124
  -2.000   0.2142   0.00772   0.00162  -0.0907   0.6654   0.0136
  -1.750   0.2392   0.00763   0.00135  -0.0898   0.6348   0.0171
  -1.500   0.2643   0.00743   0.00118  -0.0891   0.6084   0.0551
  -1.250   0.2896   0.00728   0.00111  -0.0885   0.5847   0.1105
  -1.000   0.3146   0.00708   0.00107  -0.0880   0.5639   0.1981
  -0.750   0.3399   0.00685   0.00106  -0.0876   0.5461   0.2999
  -0.500   0.3649   0.00660   0.00107  -0.0870   0.5294   0.4230
  -0.250   0.3895   0.00636   0.00111  -0.0864   0.5137   0.5503
   0.000   0.4143   0.00621   0.00116  -0.0857   0.4996   0.6528
   0.250   0.4377   0.00600   0.00118  -0.0846   0.4873   0.7536
   0.500   0.4866   0.00562   0.00121  -0.0892   0.4722   1.0000
   0.750   0.5126   0.00572   0.00123  -0.0887   0.4605   1.0000
   1.000   0.5387   0.00584   0.00125  -0.0881   0.4489   1.0000
   1.250   0.5650   0.00594   0.00128  -0.0877   0.4376   1.0000
   1.500   0.5914   0.00603   0.00132  -0.0873   0.4277   1.0000
   1.750   0.6176   0.00614   0.00136  -0.0868   0.4183   1.0000
   2.000   0.6439   0.00625   0.00142  -0.0864   0.4090   1.0000
   2.250   0.6704   0.00635   0.00148  -0.0860   0.4005   1.0000
   2.500   0.6966   0.00647   0.00154  -0.0856   0.3920   1.0000
   2.750   0.7232   0.00657   0.00161  -0.0852   0.3835   1.0000
   3.000   0.7495   0.00669   0.00170  -0.0848   0.3749   1.0000
   3.250   0.7757   0.00682   0.00178  -0.0844   0.3660   1.0000
   3.500   0.8022   0.00693   0.00187  -0.0840   0.3576   1.0000
   3.750   0.8283   0.00707   0.00197  -0.0836   0.3491   1.0000
   4.000   0.8547   0.00718   0.00209  -0.0832   0.3413   1.0000
   4.250   0.8809   0.00732   0.00220  -0.0828   0.3332   1.0000
   4.750   0.9330   0.00761   0.00244  -0.0820   0.3124   1.0000
   5.000   0.9590   0.00776   0.00259  -0.0816   0.3032   1.0000
   5.250   0.9847   0.00794   0.00274  -0.0812   0.2933   1.0000
   5.500   1.0103   0.00813   0.00290  -0.0807   0.2813   1.0000
   5.750   1.0356   0.00835   0.00308  -0.0802   0.2659   1.0000
   6.000   1.0605   0.00860   0.00328  -0.0797   0.2466   1.0000
   6.250   1.0843   0.00898   0.00353  -0.0789   0.2182   1.0000
   6.500   1.1079   0.00937   0.00381  -0.0782   0.1928   1.0000
   6.750   1.1312   0.00979   0.00412  -0.0775   0.1703   1.0000
   7.000   1.1542   0.01024   0.00446  -0.0767   0.1460   1.0000
   7.250   1.1758   0.01083   0.00490  -0.0757   0.1159   1.0000
   7.500   1.1967   0.01150   0.00540  -0.0746   0.0850   1.0000
   7.750   1.2167   0.01224   0.00597  -0.0733   0.0567   1.0000
   8.000   1.2342   0.01325   0.00675  -0.0717   0.0228   1.0000
   8.250   1.2527   0.01415   0.00756  -0.0701   0.0081   1.0000
   8.500   1.2746   0.01466   0.00813  -0.0691   0.0069   1.0000
   8.750   1.2954   0.01528   0.00880  -0.0679   0.0059   1.0000
   9.000   1.3148   0.01602   0.00966  -0.0665   0.0054   1.0000
   9.250   1.3351   0.01662   0.01035  -0.0653   0.0052   1.0000
   9.500   1.3541   0.01733   0.01115  -0.0638   0.0050   1.0000
   9.750   1.3719   0.01811   0.01202  -0.0622   0.0048   1.0000
  10.000   1.3887   0.01893   0.01295  -0.0605   0.0046   1.0000
  10.250   1.4050   0.01975   0.01386  -0.0588   0.0044   1.0000
  10.500   1.4196   0.02064   0.01485  -0.0568   0.0043   1.0000
  10.750   1.4324   0.02161   0.01591  -0.0547   0.0041   1.0000
  11.000   1.4427   0.02267   0.01708  -0.0521   0.0040   1.0000
  11.250   1.4491   0.02375   0.01826  -0.0489   0.0040   1.0000
  11.500   1.4517   0.02489   0.01950  -0.0452   0.0039   1.0000
  11.750   1.4524   0.02617   0.02089  -0.0415   0.0039   1.0000
  12.000   1.4513   0.02763   0.02246  -0.0380   0.0038   1.0000
  12.250   1.4455   0.02954   0.02448  -0.0345   0.0037   1.0000
  12.500   1.4418   0.03151   0.02658  -0.0319   0.0037   1.0000
  12.750   1.4363   0.03390   0.02909  -0.0300   0.0037   1.0000
  13.000   1.4294   0.03679   0.03211  -0.0287   0.0037   1.0000
  13.250   1.4195   0.04041   0.03586  -0.0283   0.0036   1.0000
  13.500   1.4134   0.04400   0.03961  -0.0285   0.0036   1.0000
  13.750   1.4061   0.04803   0.04376  -0.0293   0.0036   1.0000
  14.000   1.3937   0.05291   0.04879  -0.0305   0.0035   1.0000
  14.250   1.3814   0.05794   0.05396  -0.0318   0.0035   1.0000
  14.500   1.3753   0.06231   0.05845  -0.0334   0.0035   1.0000
  14.750   1.3656   0.06727   0.06353  -0.0351   0.0035   1.0000
  15.000   1.3486   0.07336   0.06978  -0.0372   0.0035   1.0000
  15.250   1.3384   0.07873   0.07527  -0.0394   0.0035   1.0000
  15.500   1.3221   0.08524   0.08193  -0.0421   0.0034   1.0000
  15.750   1.3164   0.09034   0.08713  -0.0447   0.0035   1.0000
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