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NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il)
Reynolds number: 50,000
Max Cl/Cd: 24.54 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20406-il-50000-n5.txt
Download as CSV file: xf-sc20406-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0406 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5484   0.10584   0.09897   0.0010   1.0000   0.0488
  -9.750  -0.6672   0.11154   0.10438   0.0115   1.0000   0.0491
  -9.500  -0.6647   0.10702   0.09990   0.0098   1.0000   0.0475
  -9.250  -0.6638   0.10226   0.09518   0.0074   1.0000   0.0460
  -9.000  -0.6642   0.09719   0.09017   0.0043   1.0000   0.0447
  -8.750  -0.6661   0.09165   0.08469   0.0002   1.0000   0.0433
  -8.500  -0.6699   0.08483   0.07792  -0.0068   1.0000   0.0418
  -8.000  -0.6722   0.07107   0.06374  -0.0196   1.0000   0.0387
  -7.750  -0.6658   0.06607   0.05857  -0.0218   1.0000   0.0385
  -7.500  -0.6570   0.06103   0.05321  -0.0241   1.0000   0.0386
  -7.000  -0.6313   0.05250   0.04429  -0.0269   1.0000   0.0415
  -6.750  -0.6138   0.04866   0.04010  -0.0281   1.0000   0.0432
  -6.500  -0.5936   0.04445   0.03541  -0.0293   1.0000   0.0439
  -6.250  -0.5707   0.04037   0.03077  -0.0302   1.0000   0.0443
  -6.000  -0.5459   0.03674   0.02657  -0.0306   1.0000   0.0452
  -5.750  -0.5197   0.03352   0.02280  -0.0308   1.0000   0.0467
  -5.500  -0.4928   0.03071   0.01937  -0.0305   1.0000   0.0489
  -5.250  -0.4668   0.02850   0.01686  -0.0302   1.0000   0.0546
  -5.000  -0.4409   0.02677   0.01487  -0.0296   1.0000   0.0628
  -4.750  -0.4160   0.02504   0.01307  -0.0289   1.0000   0.0733
  -4.500  -0.3914   0.02346   0.01139  -0.0279   1.0000   0.0867
  -4.250  -0.3664   0.02208   0.00991  -0.0272   1.0000   0.1060
  -4.000  -0.3415   0.02068   0.00846  -0.0269   1.0000   0.1298
  -3.750  -0.3156   0.01908   0.00721  -0.0273   1.0000   0.1847
  -3.500  -0.2961   0.01654   0.00656  -0.0266   1.0000   0.4981
  -3.250  -0.2829   0.01623   0.00674  -0.0217   1.0000   0.6827
  -3.000  -0.2690   0.01617   0.00672  -0.0170   1.0000   0.7624
  -2.750  -0.2592   0.01609   0.00667  -0.0111   1.0000   0.8311
  -2.500  -0.2488   0.01584   0.00636  -0.0049   1.0000   0.9013
  -2.250  -0.2059   0.01546   0.00573  -0.0064   1.0000   0.9587
  -2.000  -0.1584   0.01515   0.00513  -0.0107   1.0000   0.9817
  -1.750  -0.1170   0.01485   0.00464  -0.0141   1.0000   1.0000
  -1.500  -0.1018   0.01462   0.00429  -0.0128   1.0000   1.0000
  -1.250  -0.0835   0.01446   0.00403  -0.0119   1.0000   1.0000
  -1.000  -0.0620   0.01434   0.00382  -0.0115   1.0000   1.0000
  -0.750  -0.0382   0.01428   0.00368  -0.0115   1.0000   1.0000
  -0.500  -0.0132   0.01425   0.00360  -0.0117   1.0000   1.0000
  -0.250   0.0125   0.01426   0.00355  -0.0119   1.0000   1.0000
   0.000   0.0386   0.01429   0.00357  -0.0122   1.0000   1.0000
   0.250   0.0648   0.01435   0.00364  -0.0124   1.0000   1.0000
   0.500   0.0910   0.01443   0.00377  -0.0127   1.0000   1.0000
   0.750   0.1172   0.01454   0.00396  -0.0129   1.0000   1.0000
   1.000   0.1433   0.01468   0.00419  -0.0131   1.0000   1.0000
   1.250   0.1693   0.01484   0.00448  -0.0132   1.0000   1.0000
   1.500   0.1951   0.01503   0.00482  -0.0134   1.0000   1.0000
   1.750   0.2209   0.01525   0.00528  -0.0136   1.0000   1.0000
   2.000   0.2467   0.01550   0.00576  -0.0138   1.0000   1.0000
   2.250   0.2724   0.01580   0.00632  -0.0141   1.0000   1.0000
   2.500   0.3679   0.01557   0.00677  -0.0254   0.8805   1.0000
   2.750   0.4061   0.01655   0.00648  -0.0226   0.4549   1.0000
   3.000   0.4221   0.01925   0.00747  -0.0212   0.1821   1.0000
   3.250   0.4467   0.02080   0.00870  -0.0210   0.1288   1.0000
   3.500   0.4738   0.02225   0.01017  -0.0208   0.1033   1.0000
   3.750   0.5013   0.02375   0.01171  -0.0206   0.0830   1.0000
   4.000   0.5292   0.02552   0.01366  -0.0201   0.0703   1.0000
   4.250   0.5563   0.02723   0.01546  -0.0199   0.0585   1.0000
   4.500   0.5853   0.02952   0.01819  -0.0193   0.0536   1.0000
   4.750   0.6118   0.03161   0.02052  -0.0191   0.0483   1.0000
   5.000   0.6378   0.03427   0.02360  -0.0188   0.0442   1.0000
   5.250   0.6634   0.03744   0.02740  -0.0183   0.0424   1.0000
   5.500   0.6870   0.04106   0.03162  -0.0179   0.0417   1.0000
   5.750   0.7083   0.04504   0.03624  -0.0176   0.0413   1.0000
   6.000   0.7272   0.04935   0.04109  -0.0175   0.0413   1.0000
   6.250   0.7434   0.05402   0.04625  -0.0177   0.0416   1.0000
   6.500   0.7568   0.05892   0.05157  -0.0182   0.0420   1.0000
   6.750   0.7676   0.06400   0.05698  -0.0191   0.0426   1.0000
   7.000   0.7759   0.06916   0.06241  -0.0202   0.0433   1.0000
   7.250   0.7819   0.07431   0.06775  -0.0217   0.0440   1.0000
   7.500   0.7863   0.07940   0.07297  -0.0232   0.0448   1.0000
   7.750   0.7900   0.08435   0.07800  -0.0245   0.0455   1.0000
   8.000   0.7935   0.08927   0.08295  -0.0255   0.0460   1.0000
   8.500   0.7763   0.10419   0.09800  -0.0416   0.0539   1.0000
   9.000   0.7815   0.11404   0.10781  -0.0447   0.0582   1.0000
   9.250   0.6413   0.10946   0.10342  -0.0336   0.0554   1.0000
   9.500   0.6463   0.11389   0.10785  -0.0333   0.0583   1.0000
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