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TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 50,000
Max Cl/Cd: 16.25 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-50000.txt
Download as CSV file: xf-tsagi-r-3a-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TsAGI R-3a (12%)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3932   0.10082   0.09486   0.0106   1.0045   0.2601
  -7.500  -0.3793   0.09673   0.09084   0.0110   1.0045   0.2695
  -7.250  -0.3929   0.09479   0.08906   0.0088   1.0045   0.2819
  -7.000  -0.3921   0.09245   0.08682   0.0085   1.0045   0.2978
  -6.750  -0.3786   0.08890   0.08336   0.0097   1.0045   0.3154
  -6.500  -0.3778   0.08627   0.08085   0.0097   1.0045   0.3342
  -6.000  -0.3369   0.07890   0.07365   0.0141   1.0045   0.3799
  -5.750  -0.3455   0.07711   0.07204   0.0149   1.0045   0.4087
  -5.500  -0.3168   0.07347   0.06848   0.0177   1.0045   0.4372
  -5.250  -0.3012   0.07064   0.06578   0.0200   1.0045   0.4722
  -5.000  -0.3023   0.06909   0.06444   0.0236   1.0045   0.5169
  -4.500  -0.3269   0.04787   0.04158  -0.0277   0.9942   0.1578
  -4.250  -0.2522   0.04114   0.03397  -0.0387   0.9653   0.1384
  -4.000  -0.1824   0.03656   0.02867  -0.0474   0.9374   0.1381
  -3.750  -0.1236   0.03310   0.02454  -0.0528   0.9101   0.1414
  -3.500  -0.0818   0.03094   0.02221  -0.0549   0.8808   0.1499
  -3.250  -0.0455   0.02919   0.02013  -0.0553   0.8564   0.1632
  -3.000  -0.0168   0.02794   0.01870  -0.0545   0.8318   0.1817
  -2.750   0.0107   0.02679   0.01739  -0.0531   0.8091   0.2061
  -2.500   0.0382   0.02555   0.01618  -0.0515   0.7879   0.2386
  -2.250   0.0638   0.02425   0.01509  -0.0498   0.7687   0.2996
  -2.000   0.1512   0.02070   0.01389  -0.0522   0.7463   0.9955
  -1.750   0.1723   0.02096   0.01370  -0.0511   0.7287   0.9955
  -1.500   0.1936   0.02128   0.01364  -0.0501   0.7119   0.9955
  -1.250   0.2152   0.02167   0.01369  -0.0491   0.6957   0.9955
  -1.000   0.2374   0.02210   0.01383  -0.0482   0.6801   0.9955
  -0.750   0.2596   0.02257   0.01401  -0.0472   0.6651   0.9955
  -0.500   0.2818   0.02306   0.01423  -0.0460   0.6508   0.9955
  -0.250   0.3039   0.02353   0.01441  -0.0446   0.6370   0.9955
   0.000   0.3265   0.02417   0.01487  -0.0438   0.6216   0.9955
   0.250   0.3491   0.02490   0.01543  -0.0431   0.6070   0.9955
   0.500   0.3717   0.02564   0.01600  -0.0422   0.5932   0.9955
   0.750   0.3947   0.02628   0.01639  -0.0409   0.5809   0.9955
   1.000   0.4175   0.02712   0.01711  -0.0403   0.5670   0.9955
   1.250   0.4398   0.02818   0.01810  -0.0399   0.5540   0.9955
   1.500   0.4636   0.02897   0.01868  -0.0389   0.5447   0.9955
   1.750   0.4853   0.03028   0.02001  -0.0389   0.5329   0.9955
   2.000   0.5078   0.03143   0.02106  -0.0384   0.5235   0.9955
   2.250   0.5298   0.03262   0.02221  -0.0381   0.5137   0.9955
   2.500   0.5510   0.03407   0.02362  -0.0379   0.5054   0.9955
   2.750   0.5710   0.03583   0.02541  -0.0381   0.4976   0.9955
   3.000   0.5958   0.03667   0.02609  -0.0370   0.4919   0.9955
   3.250   0.6074   0.03975   0.02939  -0.0385   0.4834   0.9955
   3.500   0.6293   0.04104   0.03061  -0.0379   0.4769   0.9955
   3.750   0.6449   0.04345   0.03306  -0.0382   0.4714   0.9955
   4.000   0.6489   0.04748   0.03725  -0.0401   0.4655   0.9955
   4.250   0.6670   0.04930   0.03906  -0.0397   0.4597   0.9955
   4.500   0.6796   0.05196   0.04173  -0.0399   0.4545   0.9955
   4.750   0.6644   0.05823   0.04814  -0.0432   0.4516   0.9955
   5.000   0.6501   0.06390   0.05386  -0.0460   0.4501   0.9955
   5.250   0.6371   0.06902   0.05899  -0.0479   0.4515   0.9955
   5.500   0.6327   0.07333   0.06329  -0.0490   0.4533   0.9955
   5.750   0.6397   0.07730   0.06728  -0.0502   0.4574   0.9955
   6.000   0.5507   0.09212   0.08229  -0.0637   0.5820   0.9955
   6.250   0.5518   0.09364   0.08378  -0.0622   0.5654   0.9955
   6.500   0.5491   0.09541   0.08552  -0.0609   0.5505   0.9955
   6.750   0.5546   0.09804   0.08813  -0.0604   0.5391   0.9955
   7.000   0.5942   0.10231   0.09241  -0.0613   0.5281   0.9955
   7.250   0.5825   0.10345   0.09352  -0.0598   0.5134   0.9955
   7.500   0.5837   0.10597   0.09602  -0.0592   0.5022   0.9955
   7.750   0.6127   0.10974   0.09980  -0.0597   0.4931   0.9955
   8.000   0.6002   0.11148   0.10152  -0.0589   0.4824   0.9955
   8.250   0.6395   0.11627   0.10635  -0.0597   0.4744   0.9955
   8.500   0.6183   0.11708   0.10713  -0.0587   0.4628   0.9955
   8.750   0.6606   0.12259   0.11267  -0.0595   0.4566   0.9955
   9.000   0.6316   0.12279   0.11284  -0.0587   0.4466   0.9955
   9.250   0.6586   0.12697   0.11704  -0.0591   0.4404   0.9955
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