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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 200,000
Max Cl/Cd: 74.38 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4083-il-200000-n5.txt
Download as CSV file: xf-s4083-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3803   0.09270   0.08930  -0.0222   1.0000   0.0217
  -7.500  -0.3833   0.08931   0.08599  -0.0224   1.0000   0.0218
  -7.250  -0.3867   0.08485   0.08159  -0.0225   1.0000   0.0222
  -7.000  -0.3836   0.08152   0.07830  -0.0232   1.0000   0.0224
  -6.750  -0.3796   0.07818   0.07497  -0.0245   1.0000   0.0226
  -6.500  -0.3744   0.07487   0.07170  -0.0257   1.0000   0.0229
  -6.250  -0.3676   0.07113   0.06798  -0.0281   1.0000   0.0230
  -6.000  -0.3587   0.06719   0.06406  -0.0309   1.0000   0.0231
  -5.750  -0.3468   0.06244   0.05928  -0.0350   1.0000   0.0230
  -5.250  -0.3111   0.05040   0.04702  -0.0436   0.9991   0.0144
  -5.000  -0.2723   0.04367   0.04006  -0.0520   0.9945   0.0138
  -4.750  -0.2340   0.03704   0.03306  -0.0586   0.9889   0.0133
  -4.500  -0.1967   0.03075   0.02626  -0.0635   0.9828   0.0132
  -4.250  -0.1596   0.02599   0.02084  -0.0665   0.9763   0.0145
  -4.000  -0.1263   0.02278   0.01707  -0.0682   0.9682   0.0147
  -3.750  -0.0920   0.02010   0.01390  -0.0698   0.9605   0.0146
  -3.500  -0.0594   0.01808   0.01146  -0.0707   0.9506   0.0146
  -3.250  -0.0270   0.01646   0.00952  -0.0713   0.9390   0.0147
  -3.000   0.0075   0.01511   0.00794  -0.0724   0.9265   0.0148
  -2.750   0.0451   0.01387   0.00654  -0.0741   0.9119   0.0152
  -2.500   0.0890   0.01274   0.00527  -0.0774   0.8941   0.0164
  -2.250   0.1371   0.01199   0.00438  -0.0814   0.8674   0.0186
  -2.000   0.1857   0.01141   0.00362  -0.0855   0.8288   0.0262
  -1.750   0.2240   0.01091   0.00299  -0.0874   0.7840   0.0579
  -1.500   0.2524   0.01041   0.00276  -0.0876   0.7407   0.1782
  -1.250   0.2772   0.01006   0.00266  -0.0870   0.7032   0.3137
  -1.000   0.3006   0.00981   0.00261  -0.0861   0.6711   0.4421
  -0.750   0.3224   0.00953   0.00261  -0.0846   0.6433   0.5859
  -0.500   0.3439   0.00928   0.00258  -0.0829   0.6198   0.7128
   0.000   0.4164   0.00908   0.00239  -0.0857   0.5752   1.0000
   0.250   0.4419   0.00925   0.00236  -0.0851   0.5576   1.0000
   0.500   0.4675   0.00942   0.00235  -0.0845   0.5416   1.0000
   0.750   0.4932   0.00959   0.00237  -0.0839   0.5269   1.0000
   1.000   0.5190   0.00976   0.00240  -0.0834   0.5131   1.0000
   1.250   0.5449   0.00993   0.00244  -0.0829   0.5005   1.0000
   1.500   0.5707   0.01011   0.00251  -0.0824   0.4887   1.0000
   1.750   0.5966   0.01029   0.00258  -0.0819   0.4775   1.0000
   2.000   0.6225   0.01047   0.00268  -0.0814   0.4667   1.0000
   2.250   0.6485   0.01064   0.00279  -0.0809   0.4562   1.0000
   2.500   0.6744   0.01082   0.00291  -0.0805   0.4460   1.0000
   2.750   0.7001   0.01102   0.00303  -0.0800   0.4361   1.0000
   3.000   0.7260   0.01121   0.00320  -0.0795   0.4257   1.0000
   3.250   0.7519   0.01140   0.00336  -0.0790   0.4160   1.0000
   3.500   0.7775   0.01161   0.00352  -0.0785   0.4072   1.0000
   3.750   0.8033   0.01180   0.00371  -0.0781   0.3978   1.0000
   4.000   0.8290   0.01201   0.00394  -0.0776   0.3887   1.0000
   4.250   0.8544   0.01224   0.00414  -0.0771   0.3799   1.0000
   4.500   0.8801   0.01244   0.00437  -0.0766   0.3702   1.0000
   4.750   0.9054   0.01267   0.00461  -0.0761   0.3604   1.0000
   5.000   0.9305   0.01291   0.00486  -0.0755   0.3506   1.0000
   5.250   0.9556   0.01314   0.00515  -0.0750   0.3402   1.0000
   5.500   0.9808   0.01338   0.00544  -0.0744   0.3300   1.0000
   5.750   1.0056   0.01364   0.00574  -0.0738   0.3193   1.0000
   6.000   1.0301   0.01391   0.00604  -0.0732   0.3072   1.0000
   6.250   1.0544   0.01419   0.00639  -0.0725   0.2942   1.0000
   6.500   1.0785   0.01450   0.00674  -0.0718   0.2811   1.0000
   6.750   1.1023   0.01483   0.00712  -0.0711   0.2674   1.0000
   7.000   1.1259   0.01518   0.00753  -0.0704   0.2522   1.0000
   7.250   1.1488   0.01558   0.00796  -0.0695   0.2335   1.0000
   7.500   1.1696   0.01615   0.00846  -0.0685   0.2016   1.0000
   7.750   1.1881   0.01699   0.00907  -0.0672   0.1603   1.0000
   8.000   1.2065   0.01788   0.00980  -0.0660   0.1252   1.0000
   8.250   1.2243   0.01883   0.01062  -0.0646   0.0959   1.0000
   8.500   1.2404   0.01995   0.01158  -0.0631   0.0651   1.0000
   8.750   1.2556   0.02112   0.01264  -0.0614   0.0401   1.0000
   9.000   1.2686   0.02248   0.01394  -0.0594   0.0215   1.0000
   9.250   1.2817   0.02378   0.01529  -0.0573   0.0144   1.0000
   9.500   1.2951   0.02496   0.01661  -0.0553   0.0119   1.0000
   9.750   1.3084   0.02606   0.01786  -0.0533   0.0103   1.0000
  10.000   1.3183   0.02738   0.01929  -0.0510   0.0091   1.0000
  10.250   1.3258   0.02874   0.02082  -0.0484   0.0086   1.0000
  10.500   1.3306   0.03005   0.02231  -0.0454   0.0082   1.0000
  10.750   1.3333   0.03148   0.02391  -0.0423   0.0079   1.0000
  11.000   1.3339   0.03309   0.02569  -0.0394   0.0078   1.0000
  11.250   1.3323   0.03497   0.02777  -0.0367   0.0075   1.0000
  11.500   1.3296   0.03710   0.03006  -0.0346   0.0074   1.0000
  11.750   1.3254   0.03961   0.03273  -0.0330   0.0072   1.0000
  12.000   1.3208   0.04246   0.03574  -0.0322   0.0071   1.0000
  12.250   1.3152   0.04577   0.03921  -0.0320   0.0070   1.0000
  12.500   1.3098   0.04936   0.04296  -0.0324   0.0069   1.0000
  12.750   1.3045   0.05320   0.04695  -0.0332   0.0069   1.0000
  13.000   1.2977   0.05745   0.05136  -0.0343   0.0067   1.0000
  13.250   1.2913   0.06176   0.05582  -0.0356   0.0067   1.0000
  13.500   1.2850   0.06615   0.06036  -0.0369   0.0067   1.0000
  13.750   1.2776   0.07083   0.06518  -0.0385   0.0066   1.0000
  14.000   1.2703   0.07557   0.07007  -0.0402   0.0065   1.0000
  14.250   1.2625   0.08048   0.07512  -0.0420   0.0065   1.0000
  14.500   1.2544   0.08557   0.08035  -0.0440   0.0065   1.0000
  14.750   1.2465   0.09080   0.08574  -0.0461   0.0065   1.0000
  15.000   1.2378   0.09632   0.09141  -0.0486   0.0064   1.0000
  15.250   1.2292   0.10205   0.09729  -0.0512   0.0064   1.0000
  15.500   1.2204   0.10800   0.10340  -0.0540   0.0064   1.0000
  15.750   1.2111   0.11423   0.10979  -0.0572   0.0064   1.0000
  16.000   1.2014   0.12078   0.11650  -0.0606   0.0064   1.0000
  16.250   1.1912   0.12768   0.12356  -0.0644   0.0064   1.0000
  16.500   1.1804   0.13497   0.13101  -0.0685   0.0064   1.0000
  16.750   1.1685   0.14277   0.13898  -0.0731   0.0065   1.0000
  17.000   1.1563   0.15098   0.14734  -0.0780   0.0065   1.0000
  17.250   1.1422   0.16019   0.15671  -0.0836   0.0066   1.0000
  17.500   1.1260   0.17057   0.16723  -0.0898   0.0067   1.0000
  17.750   1.1052   0.18335   0.18015  -0.0974   0.0069   1.0000
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