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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 500,000
Max Cl/Cd: 42.42 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20403-il-500000.txt
Download as CSV file: xf-sc20403-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6730   0.09751   0.09533   0.0234   1.0000   0.0079
  -8.000  -0.6698   0.09355   0.09134   0.0210   1.0000   0.0080
  -7.750  -0.6665   0.08952   0.08734   0.0182   1.0000   0.0082
  -7.500  -0.6591   0.08492   0.08275   0.0134   1.0000   0.0083
  -7.250  -0.6478   0.07969   0.07752   0.0068   1.0000   0.0085
  -7.000  -0.6335   0.07412   0.07193  -0.0002   1.0000   0.0087
  -6.750  -0.6169   0.06857   0.06631  -0.0065   1.0000   0.0090
  -6.500  -0.5981   0.06313   0.06079  -0.0120   1.0000   0.0093
  -6.250  -0.5770   0.05787   0.05541  -0.0167   1.0000   0.0097
  -6.000  -0.5533   0.05291   0.05030  -0.0205   1.0000   0.0103
  -5.750  -0.5259   0.04873   0.04594  -0.0231   1.0000   0.0111
  -5.500  -0.4971   0.04586   0.04288  -0.0243   1.0000   0.0118
  -5.250  -0.4707   0.04217   0.03897  -0.0258   1.0000   0.0120
  -5.000  -0.4442   0.03836   0.03491  -0.0272   1.0000   0.0121
  -4.750  -0.4170   0.03466   0.03092  -0.0284   1.0000   0.0121
  -3.000  -0.2095   0.01158   0.00545  -0.0330   1.0000   0.0090
  -2.750  -0.1796   0.00988   0.00359  -0.0331   1.0000   0.0082
  -2.500  -0.1493   0.00878   0.00236  -0.0335   1.0000   0.0090
  -2.250  -0.1202   0.00821   0.00170  -0.0337   1.0000   0.0117
  -2.000  -0.0851   0.00542   0.00099  -0.0370   1.0000   0.6240
  -1.750  -0.0601   0.00497   0.00105  -0.0362   1.0000   0.7754
  -1.500  -0.0350   0.00486   0.00103  -0.0354   1.0000   0.8196
  -1.250  -0.0130   0.00473   0.00104  -0.0337   1.0000   0.8699
  -1.000   0.0075   0.00462   0.00101  -0.0317   1.0000   0.9065
  -0.750   0.0261   0.00448   0.00093  -0.0293   1.0000   0.9373
  -0.500   0.0437   0.00429   0.00081  -0.0268   1.0000   1.0000
  -0.250   0.0733   0.00431   0.00081  -0.0274   1.0000   1.0000
   0.000   0.1024   0.00433   0.00085  -0.0278   1.0000   1.0000
   0.250   0.1311   0.00436   0.00091  -0.0282   1.0000   1.0000
   0.500   0.1596   0.00439   0.00100  -0.0284   1.0000   1.0000
   0.750   0.1879   0.00443   0.00113  -0.0286   1.0000   1.0000
   1.000   0.2357   0.00690   0.00120  -0.0331   0.2677   1.0000
   1.250   0.2622   0.00857   0.00201  -0.0333   0.0109   1.0000
   1.500   0.2906   0.00921   0.00273  -0.0332   0.0084   1.0000
   1.750   0.3183   0.01034   0.00398  -0.0328   0.0078   1.0000
   2.000   0.3461   0.01206   0.00586  -0.0322   0.0085   1.0000
   2.250   0.3744   0.01488   0.00899  -0.0314   0.0107   1.0000
   3.750   0.5332   0.03439   0.03055  -0.0287   0.0115   1.0000
   4.000   0.5580   0.03792   0.03437  -0.0284   0.0115   1.0000
   4.250   0.5824   0.04157   0.03828  -0.0283   0.0114   1.0000
   4.500   0.6069   0.04524   0.04219  -0.0284   0.0113   1.0000
   4.750   0.6333   0.04839   0.04555  -0.0286   0.0109   1.0000
   5.000   0.6617   0.05156   0.04890  -0.0291   0.0100   1.0000
   5.250   0.6859   0.05601   0.05353  -0.0305   0.0094   1.0000
   5.500   0.7076   0.06086   0.05853  -0.0326   0.0088   1.0000
   5.750   0.7273   0.06591   0.06371  -0.0354   0.0084   1.0000
   6.000   0.7450   0.07111   0.06901  -0.0387   0.0081   1.0000
   6.250   0.7608   0.07638   0.07435  -0.0427   0.0078   1.0000
   6.500   0.7744   0.08167   0.07971  -0.0470   0.0076   1.0000
   6.750   0.7858   0.08693   0.08500  -0.0518   0.0075   1.0000
   7.000   0.7948   0.09209   0.09019  -0.0567   0.0073   1.0000
   7.250   0.8012   0.09707   0.09522  -0.0616   0.0072   1.0000
   7.500   0.8024   0.10149   0.09962  -0.0653   0.0071   1.0000
   7.750   0.8034   0.10575   0.10386  -0.0680   0.0070   1.0000
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