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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 50,000
Max Cl/Cd: 18.03 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20403-il-50000.txt
Download as CSV file: xf-sc20403-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.7061   0.12513   0.11846   0.0284   1.0000   0.1407
  -9.000  -0.6924   0.11938   0.11255   0.0302   1.0000   0.1488
  -8.750  -0.7010   0.11750   0.11077   0.0261   1.0000   0.1538
  -8.500  -0.6885   0.11224   0.10552   0.0277   1.0000   0.1638
  -8.250  -0.6888   0.10862   0.10198   0.0259   1.0000   0.1703
  -8.000  -0.6920   0.10595   0.09939   0.0231   1.0000   0.1798
  -7.750  -0.6843   0.10158   0.09506   0.0236   1.0000   0.1916
  -7.500  -0.6792   0.09762   0.09114   0.0227   1.0000   0.2043
  -7.250  -0.6773   0.09401   0.08760   0.0191   1.0000   0.2191
  -7.000  -0.6670   0.08983   0.08345   0.0221   1.0000   0.2415
  -6.750  -0.6614   0.08626   0.07994   0.0224   1.0000   0.2690
  -6.500  -0.6542   0.08276   0.07649   0.0252   1.0000   0.3044
  -6.250  -0.6493   0.07987   0.07366   0.0280   1.0000   0.3498
  -6.000  -0.6427   0.07705   0.07090   0.0335   1.0000   0.4034
  -5.750  -0.6251   0.07350   0.06737   0.0426   1.0000   0.4649
  -4.500  -0.4346   0.03880   0.02990  -0.0310   1.0000   0.1526
  -4.250  -0.3924   0.03490   0.02485  -0.0326   1.0000   0.1148
  -4.000  -0.3594   0.03129   0.02068  -0.0328   1.0000   0.1004
  -3.750  -0.3273   0.02805   0.01659  -0.0325   1.0000   0.0918
  -3.500  -0.2955   0.02593   0.01380  -0.0317   1.0000   0.0886
  -3.250  -0.2678   0.02341   0.01113  -0.0305   1.0000   0.0902
  -3.000  -0.2431   0.02143   0.00919  -0.0291   1.0000   0.1069
  -2.750  -0.2168   0.01968   0.00734  -0.0277   1.0000   0.1273
  -2.500  -0.1873   0.01695   0.00523  -0.0278   1.0000   0.2090
  -2.250  -0.1866   0.01347   0.00436  -0.0167   1.0000   1.0000
  -2.000  -0.1589   0.01336   0.00356  -0.0167   1.0000   1.0000
  -1.750  -0.1314   0.01327   0.00301  -0.0169   1.0000   1.0000
  -1.500  -0.1039   0.01320   0.00261  -0.0172   1.0000   1.0000
  -1.250  -0.0765   0.01315   0.00230  -0.0173   1.0000   1.0000
  -1.000  -0.0492   0.01311   0.00200  -0.0175   1.0000   1.0000
  -0.750  -0.0219   0.01309   0.00183  -0.0176   1.0000   1.0000
  -0.500   0.0052   0.01309   0.00173  -0.0177   1.0000   1.0000
  -0.250   0.0322   0.01310   0.00169  -0.0177   1.0000   1.0000
   0.000   0.0591   0.01312   0.00173  -0.0177   1.0000   1.0000
   0.250   0.0860   0.01315   0.00183  -0.0177   1.0000   1.0000
   0.500   0.1127   0.01319   0.00200  -0.0176   1.0000   1.0000
   0.750   0.1394   0.01325   0.00224  -0.0175   1.0000   1.0000
   1.000   0.1661   0.01333   0.00262  -0.0174   1.0000   1.0000
   1.250   0.1926   0.01341   0.00301  -0.0172   1.0000   1.0000
   1.500   0.2192   0.01352   0.00352  -0.0170   1.0000   1.0000
   1.750   0.2459   0.01364   0.00423  -0.0167   1.0000   1.0000
   2.000   0.3088   0.01939   0.00721  -0.0203   0.1293   1.0000
   2.250   0.3393   0.02141   0.00932  -0.0195   0.1104   1.0000
   2.500   0.3693   0.02356   0.01146  -0.0192   0.0892   1.0000
   2.750   0.4002   0.02619   0.01431  -0.0185   0.0875   1.0000
   3.000   0.4322   0.02841   0.01717  -0.0176   0.0908   1.0000
   3.250   0.4638   0.03155   0.02087  -0.0169   0.0989   1.0000
   3.500   0.4955   0.03521   0.02540  -0.0163   0.1137   1.0000
   3.750   0.5338   0.03874   0.03008  -0.0162   0.1507   1.0000
   4.000   0.6438   0.05337   0.04774  -0.0983   0.7359   1.0000
   4.250   0.6150   0.05564   0.04983  -0.1002   0.7999   1.0000
   4.500   0.6009   0.05805   0.05214  -0.0998   0.8271   1.0000
   5.500   0.7469   0.07596   0.07044  -0.0596   0.3601   1.0000
   5.750   0.7536   0.07947   0.07387  -0.0538   0.3085   1.0000
   6.000   0.7597   0.08320   0.07754  -0.0511   0.2687   1.0000
   6.250   0.7656   0.08703   0.08135  -0.0510   0.2383   1.0000
   6.500   0.7728   0.09139   0.08566  -0.0504   0.2164   1.0000
   6.750   0.7774   0.09545   0.08971  -0.0528   0.1990   1.0000
   7.000   0.7822   0.09975   0.09398  -0.0547   0.1860   1.0000
   7.250   0.7868   0.10419   0.09839  -0.0564   0.1759   1.0000
   7.500   0.7957   0.10914   0.10331  -0.0555   0.1656   1.0000
   7.750   0.7900   0.11219   0.10629  -0.0605   0.1584   1.0000
   8.000   0.7955   0.11695   0.11102  -0.0609   0.1517   1.0000
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