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SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SOKOLOV AIRFOIL (sokolov-il)
Reynolds number: 100,000
Max Cl/Cd: 68.73 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sokolov-il-100000.txt
Download as CSV file: xf-sokolov-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SOKOLOV AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2984   0.10091   0.09651  -0.0269   1.0000   0.0620
  -6.750  -0.3103   0.10087   0.09660  -0.0265   1.0000   0.0626
  -6.500  -0.3203   0.10086   0.09672  -0.0276   1.0000   0.0630
  -6.250  -0.3240   0.10039   0.09633  -0.0308   1.0000   0.0633
  -6.000  -0.3288   0.09631   0.09230  -0.0261   1.0000   0.0639
  -5.750  -0.3321   0.09304   0.08909  -0.0200   1.0000   0.0655
  -5.500  -0.3346   0.09123   0.08733  -0.0179   1.0000   0.0677
  -5.250  -0.2683   0.08730   0.08328  -0.0448   0.9918   0.0757
  -5.000  -0.2640   0.08216   0.07818  -0.0376   0.9874   0.0778
  -4.750  -0.2272   0.07793   0.07388  -0.0446   0.9815   0.0844
  -4.500  -0.1769   0.07258   0.06844  -0.0587   0.9734   0.0899
  -4.250  -0.1338   0.06856   0.06431  -0.0669   0.9674   0.0992
  -4.000  -0.0972   0.06402   0.05972  -0.0734   0.9598   0.1057
  -3.750  -0.0346   0.05875   0.05428  -0.0876   0.9556   0.1171
  -3.500   0.0179   0.05447   0.04982  -0.0986   0.9467   0.1298
  -3.250   0.0660   0.05048   0.04570  -0.1060   0.9425   0.1449
  -3.000   0.1095   0.04711   0.04220  -0.1124   0.9344   0.1597
  -2.750   0.1588   0.04371   0.03867  -0.1192   0.9297   0.1762
  -2.000   0.3716   0.02782   0.02066  -0.1532   0.9179   0.1103
  -1.750   0.4242   0.02547   0.01773  -0.1582   0.9142   0.1109
  -1.500   0.4636   0.02386   0.01572  -0.1604   0.9057   0.1088
  -1.250   0.5079   0.02239   0.01387  -0.1633   0.9004   0.1099
  -1.000   0.5429   0.02155   0.01274  -0.1643   0.8911   0.1134
  -0.750   0.5822   0.02045   0.01162  -0.1662   0.8854   0.1239
  -0.500   0.6126   0.01982   0.01100  -0.1666   0.8752   0.1373
  -0.250   0.6474   0.01891   0.01021  -0.1675   0.8679   0.1658
   0.000   0.6803   0.01800   0.00976  -0.1681   0.8589   0.2942
   0.250   0.7082   0.01739   0.00980  -0.1677   0.8485   0.5298
   0.500   0.7305   0.01644   0.00943  -0.1656   0.8389   1.0000
   0.750   0.7595   0.01649   0.00924  -0.1652   0.8292   1.0000
   1.000   0.7862   0.01671   0.00928  -0.1647   0.8181   1.0000
   1.250   0.8137   0.01688   0.00929  -0.1642   0.8080   1.0000
   1.500   0.8420   0.01693   0.00920  -0.1636   0.7991   1.0000
   1.750   0.8677   0.01723   0.00942  -0.1630   0.7878   1.0000
   2.000   0.8944   0.01753   0.00965  -0.1626   0.7784   1.0000
   2.250   0.9222   0.01769   0.00971  -0.1621   0.7703   1.0000
   2.500   0.9477   0.01805   0.01008  -0.1617   0.7597   1.0000
   2.750   0.9742   0.01831   0.01031  -0.1611   0.7505   1.0000
   3.000   1.0014   0.01847   0.01041  -0.1606   0.7416   1.0000
   3.250   1.0267   0.01879   0.01077  -0.1600   0.7307   1.0000
   3.500   1.0528   0.01902   0.01104  -0.1593   0.7205   1.0000
   3.750   1.0802   0.01909   0.01107  -0.1586   0.7113   1.0000
   4.000   1.1054   0.01936   0.01140  -0.1579   0.6997   1.0000
   4.250   1.1308   0.01966   0.01177  -0.1573   0.6889   1.0000
   4.500   1.1573   0.01988   0.01208  -0.1567   0.6793   1.0000
   4.750   1.1841   0.02006   0.01230  -0.1561   0.6694   1.0000
   5.000   1.2091   0.02034   0.01271  -0.1553   0.6572   1.0000
   5.250   1.2345   0.02055   0.01302  -0.1545   0.6445   1.0000
   5.500   1.2599   0.02075   0.01335  -0.1536   0.6314   1.0000
   5.750   1.2852   0.02073   0.01340  -0.1524   0.6152   1.0000
   6.000   1.3097   0.02048   0.01316  -0.1507   0.5939   1.0000
   6.250   1.3328   0.02019   0.01284  -0.1488   0.5678   1.0000
   6.500   1.3545   0.02020   0.01302  -0.1471   0.5419   1.0000
   6.750   1.3751   0.02015   0.01300  -0.1450   0.5095   1.0000
   7.000   1.3897   0.02022   0.01303  -0.1419   0.4457   1.0000
   7.250   1.3948   0.02143   0.01346  -0.1376   0.3301   1.0000
   7.500   1.3847   0.02487   0.01552  -0.1323   0.1545   1.0000
   7.750   1.3820   0.02793   0.01785  -0.1278   0.0726   1.0000
   8.000   1.3874   0.02992   0.01984  -0.1243   0.0612   1.0000
   8.250   1.3885   0.03201   0.02197  -0.1205   0.0550   1.0000
   8.500   1.3931   0.03363   0.02379  -0.1170   0.0511   1.0000
   8.750   1.3939   0.03543   0.02573  -0.1131   0.0488   1.0000
   9.000   1.3952   0.03743   0.02780  -0.1096   0.0471   1.0000
   9.250   1.3984   0.03962   0.03002  -0.1064   0.0455   1.0000
   9.500   1.4114   0.04215   0.03248  -0.1041   0.0440   1.0000
   9.750   1.4419   0.04454   0.03491  -0.1035   0.0427   1.0000
  10.000   1.4655   0.04662   0.03723  -0.1025   0.0408   1.0000
  10.250   1.4978   0.04959   0.04049  -0.1027   0.0396   1.0000
  10.500   1.5281   0.05345   0.04471  -0.1027   0.0399   1.0000
  10.750   1.5450   0.05746   0.04913  -0.1012   0.0405   1.0000
  11.000   1.5542   0.06176   0.05382  -0.0990   0.0414   1.0000
  11.250   1.5598   0.06669   0.05911  -0.0968   0.0424   1.0000
  11.500   1.5752   0.07237   0.06506  -0.0959   0.0440   1.0000
  11.750   1.5587   0.07350   0.06664  -0.0902   0.0454   1.0000
  12.000   1.5263   0.07659   0.07021  -0.0847   0.0464   1.0000
  12.250   1.4973   0.08109   0.07516  -0.0813   0.0477   1.0000
  12.500   1.4717   0.08623   0.08064  -0.0794   0.0489   1.0000
  12.750   1.4476   0.09171   0.08640  -0.0788   0.0499   1.0000
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