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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.47 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2050-il-1000000.txt
Download as CSV file: xf-s2050-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2050 8.93%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6133   0.08898   0.08732  -0.0195   1.0000   0.0086
 -10.750  -0.7118   0.06133   0.05967  -0.0355   1.0000   0.0075
 -10.500  -0.8334   0.03797   0.03562  -0.0510   1.0000   0.0066
 -10.250  -0.8267   0.03683   0.03444  -0.0498   1.0000   0.0068
 -10.000  -0.8515   0.03067   0.02773  -0.0476   1.0000   0.0066
  -9.750  -0.8478   0.02779   0.02455  -0.0460   1.0000   0.0066
  -9.500  -0.8385   0.02539   0.02188  -0.0446   1.0000   0.0066
  -9.250  -0.8247   0.02356   0.01985  -0.0434   1.0000   0.0067
  -9.000  -0.8096   0.02165   0.01771  -0.0422   1.0000   0.0067
  -8.750  -0.7921   0.02011   0.01597  -0.0412   1.0000   0.0067
  -8.500  -0.7736   0.01857   0.01421  -0.0402   1.0000   0.0068
  -8.250  -0.7533   0.01738   0.01288  -0.0394   1.0000   0.0069
  -8.000  -0.7319   0.01646   0.01184  -0.0386   1.0000   0.0070
  -7.750  -0.7100   0.01559   0.01086  -0.0378   1.0000   0.0073
  -7.500  -0.6876   0.01473   0.00990  -0.0371   1.0000   0.0075
  -7.250  -0.6649   0.01385   0.00891  -0.0364   1.0000   0.0076
  -7.000  -0.6417   0.01304   0.00799  -0.0358   1.0000   0.0078
  -6.750  -0.6180   0.01234   0.00720  -0.0352   1.0000   0.0080
  -6.500  -0.5939   0.01176   0.00654  -0.0346   1.0000   0.0083
  -6.250  -0.5634   0.01130   0.00601  -0.0353   0.9993   0.0086
  -6.000  -0.5297   0.01037   0.00496  -0.0369   0.9979   0.0096
  -5.750  -0.4947   0.00997   0.00452  -0.0386   0.9964   0.0105
  -5.500  -0.4592   0.00963   0.00414  -0.0403   0.9950   0.0115
  -5.250  -0.4244   0.00920   0.00368  -0.0419   0.9936   0.0139
  -5.000  -0.3912   0.00869   0.00326  -0.0432   0.9914   0.0281
  -4.750  -0.3566   0.00838   0.00301  -0.0448   0.9892   0.0423
  -4.500  -0.3209   0.00812   0.00282  -0.0466   0.9872   0.0545
  -4.250  -0.2842   0.00789   0.00264  -0.0486   0.9855   0.0678
  -4.000  -0.2468   0.00765   0.00246  -0.0507   0.9841   0.0834
  -3.750  -0.2153   0.00740   0.00228  -0.0515   0.9803   0.1017
  -3.500  -0.1815   0.00710   0.00210  -0.0529   0.9768   0.1288
  -3.250  -0.1454   0.00683   0.00193  -0.0548   0.9741   0.1576
  -3.000  -0.1078   0.00652   0.00176  -0.0570   0.9720   0.1953
  -2.750  -0.0773   0.00619   0.00159  -0.0576   0.9656   0.2409
  -2.500  -0.0437   0.00582   0.00142  -0.0589   0.9597   0.3008
  -2.250  -0.0131   0.00539   0.00126  -0.0597   0.9501   0.3818
  -2.000   0.0211   0.00495   0.00110  -0.0611   0.9393   0.4736
  -1.750   0.0552   0.00457   0.00098  -0.0625   0.9228   0.5637
  -1.500   0.0869   0.00443   0.00091  -0.0632   0.8985   0.6221
  -1.250   0.1151   0.00445   0.00088  -0.0630   0.8685   0.6465
  -1.000   0.1420   0.00453   0.00086  -0.0626   0.8380   0.6665
  -0.750   0.1686   0.00462   0.00086  -0.0621   0.8092   0.6809
  -0.500   0.1952   0.00472   0.00087  -0.0616   0.7817   0.6940
  -0.250   0.2218   0.00482   0.00089  -0.0612   0.7556   0.7065
   0.000   0.2488   0.00491   0.00091  -0.0609   0.7309   0.7171
   0.250   0.2759   0.00501   0.00093  -0.0606   0.7073   0.7269
   0.750   0.3300   0.00521   0.00099  -0.0600   0.6577   0.7439
   1.250   0.3837   0.00543   0.00109  -0.0594   0.6029   0.7631
   1.500   0.4107   0.00558   0.00115  -0.0591   0.5734   0.7719
   1.750   0.4373   0.00572   0.00121  -0.0588   0.5418   0.7805
   2.000   0.4640   0.00588   0.00130  -0.0585   0.5116   0.7893
   2.250   0.4908   0.00605   0.00138  -0.0582   0.4813   0.7982
   2.500   0.5174   0.00621   0.00147  -0.0579   0.4510   0.8060
   2.750   0.5441   0.00642   0.00158  -0.0577   0.4183   0.8144
   3.000   0.5700   0.00665   0.00170  -0.0573   0.3784   0.8228
   3.250   0.5964   0.00687   0.00183  -0.0570   0.3467   0.8323
   3.500   0.6228   0.00708   0.00197  -0.0567   0.3185   0.8424
   3.750   0.6485   0.00733   0.00213  -0.0563   0.2829   0.8521
   4.000   0.6737   0.00765   0.00231  -0.0559   0.2415   0.8630
   4.250   0.6990   0.00794   0.00250  -0.0554   0.2082   0.8755
   4.500   0.7234   0.00824   0.00271  -0.0547   0.1758   0.8902
   4.750   0.7471   0.00852   0.00294  -0.0539   0.1476   0.9080
   5.000   0.7693   0.00878   0.00315  -0.0527   0.1230   0.9317
   5.250   0.7928   0.00901   0.00334  -0.0517   0.0996   0.9791
   5.500   0.8202   0.00940   0.00362  -0.0518   0.0771   1.0000
   5.750   0.8462   0.00981   0.00393  -0.0516   0.0583   1.0000
   6.000   0.8721   0.01022   0.00426  -0.0514   0.0421   1.0000
   6.250   0.8970   0.01078   0.00470  -0.0510   0.0245   1.0000
   6.500   0.9221   0.01129   0.00518  -0.0505   0.0187   1.0000
   6.750   0.9481   0.01166   0.00560  -0.0502   0.0171   1.0000
   7.000   0.9735   0.01211   0.00605  -0.0498   0.0156   1.0000
   7.250   0.9971   0.01282   0.00684  -0.0491   0.0139   1.0000
   7.500   1.0220   0.01328   0.00736  -0.0487   0.0135   1.0000
   7.750   1.0467   0.01377   0.00791  -0.0482   0.0131   1.0000
   8.000   1.0708   0.01431   0.00852  -0.0476   0.0125   1.0000
   8.250   1.0944   0.01490   0.00917  -0.0470   0.0121   1.0000
   8.500   1.1176   0.01553   0.00986  -0.0463   0.0116   1.0000
   8.750   1.1406   0.01615   0.01053  -0.0456   0.0112   1.0000
   9.000   1.1620   0.01695   0.01139  -0.0447   0.0106   1.0000
   9.250   1.1770   0.01862   0.01321  -0.0429   0.0100   1.0000
   9.500   1.1956   0.01979   0.01451  -0.0417   0.0097   1.0000
   9.750   1.2174   0.02045   0.01525  -0.0409   0.0095   1.0000
  10.000   1.2378   0.02127   0.01616  -0.0399   0.0093   1.0000
  10.250   1.2566   0.02225   0.01725  -0.0387   0.0090   1.0000
  10.500   1.2753   0.02318   0.01828  -0.0376   0.0087   1.0000
  10.750   1.2934   0.02410   0.01929  -0.0364   0.0084   1.0000
  11.000   1.3106   0.02503   0.02031  -0.0352   0.0081   1.0000
  11.250   1.3278   0.02584   0.02119  -0.0340   0.0078   1.0000
  11.500   1.3421   0.02689   0.02233  -0.0325   0.0076   1.0000
  11.750   1.3535   0.02812   0.02365  -0.0306   0.0074   1.0000
  12.000   1.3573   0.02972   0.02536  -0.0278   0.0072   1.0000
  12.250   1.3488   0.03216   0.02799  -0.0237   0.0070   1.0000
  12.500   1.3259   0.03615   0.03227  -0.0192   0.0068   1.0000
  12.750   1.3219   0.03830   0.03459  -0.0170   0.0068   1.0000
  13.000   1.3221   0.04019   0.03660  -0.0158   0.0067   1.0000
  13.250   1.3195   0.04262   0.03918  -0.0150   0.0066   1.0000
  13.500   1.3111   0.04606   0.04277  -0.0149   0.0066   1.0000
  13.750   1.3076   0.04924   0.04609  -0.0156   0.0065   1.0000
  14.000   1.2958   0.05397   0.05098  -0.0173   0.0065   1.0000
  14.250   1.2826   0.05942   0.05660  -0.0199   0.0064   1.0000
  14.500   1.2690   0.06550   0.06283  -0.0234   0.0064   1.0000
  14.750   1.2514   0.07283   0.07032  -0.0279   0.0064   1.0000
  15.000   1.2284   0.08174   0.07941  -0.0336   0.0064   1.0000
  15.250   1.2046   0.09140   0.08923  -0.0398   0.0064   1.0000
  15.500   1.1777   0.10230   0.10028  -0.0467   0.0065   1.0000
  15.750   1.1459   0.11495   0.11309  -0.0546   0.0066   1.0000
  16.000   1.0990   0.13231   0.13062  -0.0653   0.0067   1.0000
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