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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 1,000,000
Max Cl/Cd: 39.87 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20403-il-1000000-n5.txt
Download as CSV file: xf-sc20403-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0403 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5516   0.08066   0.07916   0.0099   1.0000   0.0051
  -7.750  -0.5524   0.07639   0.07491   0.0084   1.0000   0.0051
  -7.500  -0.5539   0.07216   0.07069   0.0066   1.0000   0.0051
  -7.250  -0.5554   0.06776   0.06630   0.0038   1.0000   0.0051
  -7.000  -0.5510   0.06212   0.06066  -0.0026   1.0000   0.0051
  -6.750  -0.5432   0.05626   0.05476  -0.0085   1.0000   0.0051
  -6.500  -0.5328   0.05055   0.04899  -0.0130   1.0000   0.0051
  -6.250  -0.5198   0.04498   0.04334  -0.0167   1.0000   0.0052
  -6.000  -0.5045   0.03959   0.03785  -0.0197   1.0000   0.0052
  -5.750  -0.4870   0.03446   0.03258  -0.0222   1.0000   0.0052
  -5.500  -0.4678   0.02957   0.02755  -0.0241   1.0000   0.0052
  -5.250  -0.4467   0.02501   0.02281  -0.0257   1.0000   0.0052
  -5.000  -0.4239   0.02076   0.01836  -0.0270   1.0000   0.0052
  -4.750  -0.3996   0.01698   0.01435  -0.0281   1.0000   0.0052
  -4.500  -0.3739   0.01360   0.01071  -0.0290   1.0000   0.0052
  -4.250  -0.3468   0.01067   0.00750  -0.0298   1.0000   0.0052
  -4.000  -0.3187   0.00819   0.00471  -0.0306   1.0000   0.0052
  -3.500  -0.2611   0.01227   0.00748  -0.0340   1.0000   0.0035
  -3.250  -0.2300   0.00974   0.00465  -0.0341   1.0000   0.0028
  -3.000  -0.1987   0.00806   0.00274  -0.0346   1.0000   0.0024
  -2.750  -0.1688   0.00729   0.00182  -0.0350   1.0000   0.0022
  -2.500  -0.1399   0.00687   0.00128  -0.0352   1.0000   0.0023
  -2.250  -0.1117   0.00662   0.00096  -0.0352   1.0000   0.0026
  -2.000  -0.0842   0.00648   0.00080  -0.0352   1.0000   0.0033
  -1.750  -0.0569   0.00637   0.00071  -0.0351   1.0000   0.0043
  -1.500  -0.0289   0.00604   0.00062  -0.0354   1.0000   0.0649
  -1.250   0.0033   0.00454   0.00049  -0.0376   1.0000   0.4992
  -1.000   0.0315   0.00410   0.00050  -0.0380   1.0000   0.6434
  -0.750   0.0586   0.00398   0.00052  -0.0379   1.0000   0.6831
  -0.500   0.0856   0.00384   0.00056  -0.0378   1.0000   0.7338
  -0.250   0.1261   0.00372   0.00058  -0.0407   0.9835   0.7719
   0.000   0.1514   0.00515   0.00065  -0.0400   0.5525   0.7933
   0.500   0.2031   0.00713   0.00092  -0.0402   0.0043   0.8258
   0.750   0.2304   0.00720   0.00102  -0.0401   0.0033   0.8413
   1.000   0.2577   0.00731   0.00118  -0.0399   0.0025   0.8556
   1.250   0.2850   0.00750   0.00149  -0.0396   0.0022   0.8682
   1.500   0.3122   0.00783   0.00196  -0.0393   0.0022   0.8802
   2.000   0.3648   0.00966   0.00420  -0.0379   0.0026   0.9057
   2.250   0.3900   0.01166   0.00648  -0.0364   0.0031   0.9210
   2.500   0.4149   0.01425   0.00946  -0.0347   0.0040   0.9416
   2.750   0.4396   0.01757   0.01337  -0.0330   0.0047   1.0000
   3.000   0.4657   0.02189   0.01813  -0.0322   0.0051   1.0000
   3.250   0.4921   0.02503   0.02156  -0.0316   0.0051   1.0000
   3.500   0.5180   0.02837   0.02518  -0.0311   0.0051   1.0000
   3.750   0.5433   0.03194   0.02901  -0.0306   0.0051   1.0000
   4.000   0.5680   0.03575   0.03305  -0.0303   0.0051   1.0000
   4.250   0.5922   0.03977   0.03728  -0.0302   0.0051   1.0000
   4.500   0.6158   0.04395   0.04166  -0.0304   0.0051   1.0000
   4.750   0.6388   0.04832   0.04620  -0.0309   0.0050   1.0000
   5.000   0.6610   0.05287   0.05091  -0.0319   0.0050   1.0000
   5.250   0.6822   0.05760   0.05577  -0.0333   0.0050   1.0000
   5.500   0.7022   0.06248   0.06077  -0.0352   0.0050   1.0000
   5.750   0.7210   0.06750   0.06589  -0.0377   0.0050   1.0000
   6.000   0.7383   0.07262   0.07110  -0.0407   0.0049   1.0000
   6.250   0.7540   0.07781   0.07636  -0.0443   0.0049   1.0000
   6.500   0.7678   0.08303   0.08163  -0.0484   0.0049   1.0000
   6.750   0.7798   0.08825   0.08688  -0.0529   0.0049   1.0000
   7.000   0.7897   0.09339   0.09204  -0.0577   0.0048   1.0000
   7.250   0.7974   0.09841   0.09707  -0.0627   0.0048   1.0000
   7.500   0.7989   0.10285   0.10150  -0.0666   0.0048   1.0000
   7.750   0.8004   0.10703   0.10566  -0.0694   0.0048   1.0000
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