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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 500,000
Max Cl/Cd: 33.23 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20403-il-500000-n5.txt
Download as CSV file: xf-sc20403-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6784   0.11909   0.11679   0.0307   1.0000   0.0052
  -9.250  -0.6743   0.11510   0.11281   0.0290   1.0000   0.0052
  -9.000  -0.6702   0.11110   0.10882   0.0272   1.0000   0.0052
  -8.750  -0.6662   0.10710   0.10483   0.0253   1.0000   0.0052
  -8.500  -0.6622   0.10310   0.10085   0.0233   1.0000   0.0052
  -8.250  -0.6582   0.09908   0.09685   0.0211   1.0000   0.0052
  -8.000  -0.6543   0.09504   0.09282   0.0187   1.0000   0.0052
  -7.750  -0.6499   0.09087   0.08868   0.0156   1.0000   0.0052
  -7.500  -0.6405   0.08601   0.08383   0.0103   1.0000   0.0052
  -7.250  -0.6280   0.08062   0.07843   0.0036   1.0000   0.0053
  -7.000  -0.6135   0.07517   0.07293  -0.0025   1.0000   0.0053
  -6.750  -0.5975   0.06983   0.06753  -0.0076   1.0000   0.0053
  -6.500  -0.5801   0.06460   0.06221  -0.0121   1.0000   0.0053
  -6.250  -0.5610   0.05948   0.05699  -0.0158   1.0000   0.0053
  -6.000  -0.5405   0.05452   0.05189  -0.0190   1.0000   0.0053
  -5.750  -0.5203   0.04763   0.04481  -0.0228   1.0000   0.0054
  -5.500  -0.4975   0.04142   0.03835  -0.0258   1.0000   0.0056
  -5.250  -0.4722   0.03637   0.03303  -0.0279   1.0000   0.0058
  -5.000  -0.4451   0.03200   0.02836  -0.0295   1.0000   0.0059
  -4.750  -0.4164   0.02821   0.02426  -0.0305   1.0000   0.0059
  -4.250  -0.3588   0.02319   0.01874  -0.0315   1.0000   0.0049
  -4.000  -0.3271   0.01905   0.01412  -0.0325   1.0000   0.0045
  -3.750  -0.2960   0.01607   0.01072  -0.0328   1.0000   0.0041
  -3.500  -0.2657   0.01367   0.00781  -0.0329   1.0000   0.0037
  -3.250  -0.2360   0.01172   0.00559  -0.0329   1.0000   0.0035
  -3.000  -0.2065   0.01019   0.00387  -0.0330   1.0000   0.0034
  -2.750  -0.1766   0.00909   0.00262  -0.0334   1.0000   0.0034
  -2.500  -0.1471   0.00839   0.00177  -0.0337   1.0000   0.0036
  -2.250  -0.1186   0.00802   0.00127  -0.0338   1.0000   0.0044
  -2.000  -0.0909   0.00782   0.00102  -0.0337   1.0000   0.0065
  -1.750  -0.0591   0.00622   0.00078  -0.0360   1.0000   0.3791
  -1.500  -0.0301   0.00534   0.00076  -0.0368   1.0000   0.6373
  -1.250  -0.0036   0.00503   0.00078  -0.0365   1.0000   0.7360
  -1.000   0.0220   0.00490   0.00082  -0.0359   1.0000   0.7891
  -0.750   0.0475   0.00481   0.00084  -0.0352   1.0000   0.8236
  -0.500   0.0730   0.00476   0.00086  -0.0346   1.0000   0.8459
  -0.250   0.0985   0.00471   0.00090  -0.0341   1.0000   0.8637
   0.000   0.1236   0.00467   0.00095  -0.0334   1.0000   0.8814
   0.250   0.1480   0.00462   0.00101  -0.0325   1.0000   0.8998
   0.750   0.2108   0.00779   0.00116  -0.0347   0.0736   0.9252
   1.000   0.2343   0.00817   0.00128  -0.0337   0.0049   0.9493
   1.250   0.2621   0.00834   0.00155  -0.0335   0.0039   1.0000
   1.500   0.2906   0.00881   0.00215  -0.0336   0.0034   1.0000
   1.750   0.3187   0.00959   0.00307  -0.0334   0.0032   1.0000
   2.000   0.3462   0.01079   0.00442  -0.0331   0.0033   1.0000
   2.250   0.3739   0.01237   0.00619  -0.0325   0.0034   1.0000
   2.500   0.4021   0.01441   0.00850  -0.0319   0.0037   1.0000
   2.750   0.4305   0.01679   0.01139  -0.0312   0.0040   1.0000
   3.000   0.4585   0.01968   0.01470  -0.0305   0.0044   1.0000
   3.250   0.4850   0.02376   0.01925  -0.0298   0.0049   1.0000
   5.750   0.7073   0.06756   0.06532  -0.0352   0.0051   1.0000
   6.000   0.7240   0.07268   0.07054  -0.0379   0.0051   1.0000
   6.250   0.7391   0.07787   0.07581  -0.0411   0.0051   1.0000
   6.500   0.7526   0.08308   0.08108  -0.0448   0.0051   1.0000
   6.750   0.7643   0.08830   0.08634  -0.0489   0.0051   1.0000
   7.000   0.7742   0.09345   0.09153  -0.0533   0.0051   1.0000
   7.250   0.7821   0.09852   0.09661  -0.0580   0.0051   1.0000
   7.500   0.7856   0.10314   0.10122  -0.0621   0.0051   1.0000
   7.750   0.7874   0.10750   0.10556  -0.0651   0.0051   1.0000
   8.000   0.7896   0.11179   0.10984  -0.0676   0.0051   1.0000
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