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S2046 (s2046-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 50,000
Max Cl/Cd: 38.66 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2046-il-50000.txt
Download as CSV file: xf-s2046-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3976   0.09321   0.08639  -0.0152   1.0000   0.2940
  -7.250  -0.4068   0.09186   0.08517  -0.0140   1.0000   0.3070
  -7.000  -0.3960   0.08841   0.08176  -0.0125   1.0000   0.3211
  -6.750  -0.3888   0.08532   0.07872  -0.0109   1.0000   0.3348
  -6.500  -0.3891   0.08287   0.07637  -0.0088   1.0000   0.3495
  -6.250  -0.3895   0.08051   0.07411  -0.0066   1.0000   0.3641
  -6.000  -0.4057   0.07947   0.07325  -0.0046   1.0000   0.3811
  -5.750  -0.4322   0.06269   0.05629  -0.0403   1.0000   0.2040
  -5.500  -0.4107   0.05026   0.04313  -0.0522   1.0000   0.1413
  -5.250  -0.3866   0.04333   0.03525  -0.0578   1.0000   0.1293
  -5.000  -0.3638   0.03929   0.03072  -0.0592   1.0000   0.1289
  -4.750  -0.3427   0.03634   0.02763  -0.0595   1.0000   0.1349
  -4.500  -0.3163   0.03329   0.02405  -0.0604   1.0000   0.1412
  -4.250  -0.2905   0.03057   0.02100  -0.0607   1.0000   0.1504
  -4.000  -0.2649   0.02844   0.01860  -0.0608   1.0000   0.1681
  -3.750  -0.2390   0.02651   0.01645  -0.0607   1.0000   0.1921
  -3.500  -0.2135   0.02490   0.01466  -0.0604   1.0000   0.2195
  -3.250  -0.1895   0.02352   0.01333  -0.0597   1.0000   0.2496
  -3.000  -0.1654   0.02225   0.01219  -0.0589   1.0000   0.2828
  -2.750  -0.1403   0.02113   0.01129  -0.0584   1.0000   0.3352
  -2.500  -0.1157   0.02003   0.01089  -0.0574   1.0000   0.4404
  -2.250  -0.1059   0.01961   0.01143  -0.0518   1.0000   0.6226
  -2.000  -0.1033   0.01962   0.01167  -0.0448   1.0000   0.7253
  -1.750  -0.1017   0.01941   0.01153  -0.0381   1.0000   0.7978
  -1.500  -0.1007   0.01888   0.01109  -0.0317   1.0000   0.8649
  -1.250  -0.0752   0.01807   0.01029  -0.0311   1.0000   1.0000
  -1.000  -0.0408   0.01816   0.00998  -0.0349   1.0000   1.0000
  -0.750  -0.0085   0.01838   0.00986  -0.0378   1.0000   1.0000
  -0.500   0.0215   0.01867   0.00987  -0.0399   1.0000   1.0000
  -0.250   0.0494   0.01903   0.00997  -0.0416   1.0000   1.0000
   0.000   0.0757   0.01944   0.01017  -0.0428   1.0000   1.0000
   0.250   0.1005   0.01991   0.01046  -0.0437   1.0000   1.0000
   0.500   0.1243   0.02043   0.01082  -0.0445   1.0000   1.0000
   0.750   0.1470   0.02100   0.01126  -0.0451   1.0000   1.0000
   1.000   0.1689   0.02164   0.01180  -0.0456   1.0000   1.0000
   1.250   0.1898   0.02235   0.01242  -0.0461   1.0000   1.0000
   1.500   0.2099   0.02313   0.01314  -0.0465   1.0000   1.0000
   1.750   0.2396   0.02418   0.01415  -0.0489   0.9949   1.0000
   2.000   0.3003   0.02563   0.01559  -0.0566   0.9727   1.0000
   2.250   0.3561   0.02679   0.01678  -0.0630   0.9493   1.0000
   2.500   0.4167   0.02779   0.01785  -0.0696   0.9266   1.0000
   2.750   0.4668   0.02847   0.01863  -0.0740   0.9012   1.0000
   3.000   0.5162   0.02897   0.01926  -0.0778   0.8753   1.0000
   3.250   0.5674   0.02921   0.01967  -0.0814   0.8494   1.0000
   3.500   0.6290   0.02892   0.01959  -0.0856   0.8250   1.0000
   3.750   0.6787   0.02850   0.01937  -0.0875   0.7985   1.0000
   4.250   0.7651   0.02724   0.01850  -0.0877   0.7426   1.0000
   4.500   0.8048   0.02640   0.01781  -0.0867   0.7127   1.0000
   4.750   0.8424   0.02547   0.01700  -0.0850   0.6806   1.0000
   5.000   0.8713   0.02499   0.01656  -0.0825   0.6430   1.0000
   5.250   0.9003   0.02447   0.01597  -0.0799   0.6029   1.0000
   5.500   0.9253   0.02434   0.01575  -0.0772   0.5586   1.0000
   5.750   0.9478   0.02456   0.01581  -0.0745   0.5111   1.0000
   6.000   0.9695   0.02508   0.01605  -0.0720   0.4606   1.0000
   6.250   0.9878   0.02602   0.01671  -0.0694   0.4046   1.0000
   6.500   1.0052   0.02734   0.01767  -0.0669   0.3459   1.0000
   6.750   1.0234   0.02904   0.01905  -0.0649   0.2932   1.0000
   7.000   1.0440   0.03078   0.02044  -0.0633   0.2537   1.0000
   7.250   1.0664   0.03269   0.02220  -0.0622   0.2251   1.0000
   7.500   1.0882   0.03479   0.02449  -0.0611   0.2040   1.0000
   7.750   1.1104   0.03681   0.02653  -0.0601   0.1868   1.0000
   8.000   1.1330   0.03951   0.02952  -0.0592   0.1757   1.0000
   8.250   1.1548   0.04221   0.03235  -0.0584   0.1661   1.0000
   8.500   1.1746   0.04469   0.03500  -0.0574   0.1562   1.0000
   8.750   1.1875   0.04841   0.03926  -0.0558   0.1513   1.0000
   9.000   1.1961   0.05244   0.04385  -0.0541   0.1477   1.0000
   9.250   1.2191   0.05553   0.04681  -0.0537   0.1409   1.0000
   9.500   1.2138   0.06005   0.05204  -0.0513   0.1386   1.0000
   9.750   1.2054   0.06501   0.05754  -0.0493   0.1374   1.0000
  10.000   1.1926   0.07041   0.06335  -0.0477   0.1377   1.0000
  10.250   1.1755   0.07598   0.06921  -0.0465   0.1385   1.0000
  10.500   1.1564   0.08156   0.07500  -0.0456   0.1394   1.0000
  10.750   1.1403   0.08716   0.08070  -0.0451   0.1404   1.0000
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