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NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il)
Reynolds number: 50,000
Max Cl/Cd: 20.89 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20406-il-50000.txt
Download as CSV file: xf-sc20406-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6483   0.09906   0.09234   0.0260   1.0000   0.3189
  -7.750  -0.6305   0.09454   0.08780   0.0280   1.0000   0.3395
  -7.500  -0.6388   0.09220   0.08558   0.0282   1.0000   0.3623
  -7.250  -0.6333   0.08916   0.08257   0.0300   1.0000   0.3891
  -6.250  -0.5927   0.05174   0.04379  -0.0276   1.0000   0.1513
  -6.000  -0.5625   0.04515   0.03622  -0.0311   1.0000   0.1244
  -5.750  -0.5364   0.04034   0.03096  -0.0320   1.0000   0.1171
  -5.500  -0.5081   0.03646   0.02645  -0.0329   1.0000   0.1166
  -5.250  -0.4795   0.03329   0.02274  -0.0333   1.0000   0.1211
  -5.000  -0.4493   0.03021   0.01904  -0.0333   1.0000   0.1236
  -4.750  -0.4216   0.02759   0.01619  -0.0330   1.0000   0.1358
  -4.500  -0.3937   0.02521   0.01358  -0.0322   1.0000   0.1512
  -4.250  -0.3681   0.02314   0.01151  -0.0311   1.0000   0.1786
  -4.000  -0.3434   0.02119   0.00966  -0.0294   1.0000   0.2090
  -3.750  -0.3191   0.01882   0.00797  -0.0288   1.0000   0.2904
  -3.500  -0.3263   0.01669   0.00854  -0.0171   1.0000   0.7515
  -3.250  -0.3331   0.01695   0.00881  -0.0045   1.0000   0.8626
  -3.000  -0.1990   0.01675   0.00728  -0.0183   1.0000   1.0000
  -2.750  -0.1811   0.01626   0.00659  -0.0180   1.0000   1.0000
  -2.500  -0.1638   0.01583   0.00598  -0.0175   1.0000   1.0000
  -2.250  -0.1472   0.01546   0.00547  -0.0167   1.0000   1.0000
  -2.000  -0.1317   0.01513   0.00502  -0.0155   1.0000   1.0000
  -1.750  -0.1171   0.01485   0.00461  -0.0141   1.0000   1.0000
  -1.500  -0.1019   0.01462   0.00429  -0.0128   1.0000   1.0000
  -1.250  -0.0835   0.01445   0.00403  -0.0119   1.0000   1.0000
  -1.000  -0.0619   0.01434   0.00383  -0.0116   1.0000   1.0000
  -0.750  -0.0382   0.01428   0.00368  -0.0115   1.0000   1.0000
  -0.500  -0.0132   0.01425   0.00359  -0.0117   1.0000   1.0000
  -0.250   0.0126   0.01426   0.00355  -0.0119   1.0000   1.0000
   0.000   0.0387   0.01429   0.00357  -0.0122   1.0000   1.0000
   0.250   0.0649   0.01435   0.00364  -0.0124   1.0000   1.0000
   0.500   0.0911   0.01443   0.00377  -0.0127   1.0000   1.0000
   0.750   0.1173   0.01454   0.00396  -0.0129   1.0000   1.0000
   1.000   0.1434   0.01467   0.00419  -0.0131   1.0000   1.0000
   1.250   0.1693   0.01484   0.00447  -0.0133   1.0000   1.0000
   1.500   0.1952   0.01502   0.00482  -0.0134   1.0000   1.0000
   1.750   0.2210   0.01525   0.00527  -0.0136   1.0000   1.0000
   2.000   0.2468   0.01550   0.00575  -0.0139   1.0000   1.0000
   2.250   0.2725   0.01580   0.00632  -0.0141   1.0000   1.0000
   2.500   0.2980   0.01614   0.00697  -0.0144   1.0000   1.0000
   2.750   0.3233   0.01653   0.00774  -0.0147   1.0000   1.0000
   3.000   0.3485   0.01698   0.00874  -0.0150   1.0000   1.0000
   3.250   0.4532   0.02169   0.01030  -0.0194   0.2055   1.0000
   3.500   0.4848   0.02385   0.01242  -0.0190   0.1699   1.0000
   3.750   0.5144   0.02611   0.01469  -0.0186   0.1439   1.0000
   4.000   0.5445   0.02874   0.01763  -0.0181   0.1306   1.0000
   4.250   0.5726   0.03143   0.02057  -0.0178   0.1188   1.0000
   4.500   0.6020   0.03466   0.02439  -0.0173   0.1178   1.0000
   4.750   0.6295   0.03829   0.02856  -0.0169   0.1190   1.0000
   5.000   0.6551   0.04207   0.03289  -0.0166   0.1193   1.0000
   5.250   0.6800   0.04609   0.03742  -0.0165   0.1226   1.0000
   5.500   0.7071   0.05276   0.04530  -0.0182   0.1558   1.0000
   6.250   0.7424   0.08430   0.07860  -0.0709   0.4400   1.0000
   6.500   0.7461   0.08714   0.08139  -0.0670   0.3961   1.0000
   6.750   0.7499   0.09047   0.08467  -0.0648   0.3636   1.0000
   7.000   0.7551   0.09423   0.08839  -0.0633   0.3377   1.0000
   7.250   0.7729   0.09876   0.09293  -0.0604   0.3146   1.0000
   7.500   0.7620   0.10188   0.09596  -0.0618   0.2957   1.0000
   7.750   0.7677   0.10580   0.09985  -0.0612   0.2776   1.0000
   8.000   0.7778   0.11021   0.10430  -0.0600   0.2615   1.0000
   8.250   0.7745   0.11390   0.10793  -0.0612   0.2486   1.0000
   8.500   0.7707   0.11765   0.11162  -0.0625   0.2372   1.0000
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