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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 50,000
Max Cl/Cd: 20.66 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20404-il-50000.txt
Download as CSV file: xf-sc20404-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0404 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6876   0.11145   0.10485   0.0212   1.0000   0.2009
  -8.250  -0.6819   0.10731   0.10075   0.0214   1.0000   0.2138
  -8.000  -0.6795   0.10359   0.09710   0.0210   1.0000   0.2271
  -7.750  -0.6632   0.09846   0.09197   0.0237   1.0000   0.2452
  -7.500  -0.6606   0.09511   0.08867   0.0238   1.0000   0.2638
  -7.250  -0.6577   0.09145   0.08509   0.0238   1.0000   0.2837
  -7.000  -0.6546   0.08808   0.08178   0.0238   1.0000   0.3088
  -6.750  -0.6415   0.08434   0.07805   0.0276   1.0000   0.3404
  -6.250  -0.6222   0.07771   0.07136   0.0344   1.0000   0.4197
  -6.000  -0.6114   0.07499   0.06868   0.0405   1.0000   0.4813
  -5.750  -0.5732   0.07081   0.06441   0.0485   1.0000   0.5766
  -5.250  -0.5047   0.04526   0.03699  -0.0307   1.0000   0.1590
  -5.000  -0.4636   0.03980   0.03043  -0.0342   1.0000   0.1206
  -4.750  -0.4338   0.03590   0.02609  -0.0352   1.0000   0.1190
  -4.500  -0.4024   0.03229   0.02195  -0.0358   1.0000   0.1150
  -4.250  -0.3681   0.02941   0.01817  -0.0358   1.0000   0.1077
  -4.000  -0.3381   0.02662   0.01498  -0.0353   1.0000   0.1072
  -3.750  -0.3100   0.02416   0.01228  -0.0342   1.0000   0.1103
  -3.500  -0.2842   0.02218   0.01022  -0.0324   1.0000   0.1192
  -3.250  -0.2600   0.02033   0.00850  -0.0312   1.0000   0.1523
  -3.000  -0.2316   0.01726   0.00625  -0.0312   1.0000   0.2556
  -2.750  -0.2237   0.01440   0.00583  -0.0170   1.0000   1.0000
  -2.500  -0.2037   0.01413   0.00490  -0.0163   1.0000   1.0000
  -2.250  -0.1813   0.01392   0.00429  -0.0161   1.0000   1.0000
  -2.000  -0.1566   0.01376   0.00378  -0.0162   1.0000   1.0000
  -1.750  -0.1305   0.01364   0.00336  -0.0165   1.0000   1.0000
  -1.500  -0.1037   0.01355   0.00302  -0.0169   1.0000   1.0000
  -1.250  -0.0766   0.01349   0.00276  -0.0172   1.0000   1.0000
  -1.000  -0.0493   0.01345   0.00257  -0.0175   1.0000   1.0000
  -0.750  -0.0220   0.01343   0.00240  -0.0178   1.0000   1.0000
  -0.500   0.0052   0.01343   0.00231  -0.0181   1.0000   1.0000
  -0.250   0.0323   0.01344   0.00228  -0.0183   1.0000   1.0000
   0.000   0.0593   0.01347   0.00231  -0.0184   1.0000   1.0000
   0.250   0.0862   0.01352   0.00240  -0.0185   1.0000   1.0000
   0.500   0.1130   0.01357   0.00254  -0.0186   1.0000   1.0000
   0.750   0.1397   0.01365   0.00279  -0.0186   1.0000   1.0000
   1.000   0.1663   0.01374   0.00304  -0.0186   1.0000   1.0000
   1.250   0.1928   0.01384   0.00336  -0.0186   1.0000   1.0000
   1.500   0.2193   0.01396   0.00375  -0.0186   1.0000   1.0000
   1.750   0.2457   0.01411   0.00423  -0.0185   1.0000   1.0000
   2.000   0.2721   0.01427   0.00483  -0.0183   1.0000   1.0000
   2.250   0.2987   0.01446   0.00561  -0.0181   1.0000   1.0000
   2.500   0.3743   0.02093   0.00914  -0.0226   0.1456   1.0000
   2.750   0.4056   0.02286   0.01114  -0.0223   0.1142   1.0000
   3.000   0.4365   0.02535   0.01367  -0.0218   0.1057   1.0000
   3.250   0.4681   0.02784   0.01662  -0.0211   0.1043   1.0000
   3.500   0.4987   0.03094   0.02009  -0.0206   0.1057   1.0000
   3.750   0.5314   0.03393   0.02402  -0.0198   0.1147   1.0000
   4.000   0.5631   0.03776   0.02856  -0.0195   0.1294   1.0000
   4.250   0.5930   0.04227   0.03353  -0.0196   0.1456   1.0000
   4.500   0.6418   0.05972   0.05418  -0.0994   0.7421   1.0000
   4.750   0.6231   0.06229   0.05663  -0.0998   0.7733   1.0000
   5.750   0.7627   0.07814   0.07261  -0.0631   0.3737   1.0000
   6.000   0.7738   0.08217   0.07672  -0.0573   0.3323   1.0000
   6.250   0.7729   0.08569   0.08020  -0.0585   0.2993   1.0000
   6.500   0.7785   0.08974   0.08421  -0.0577   0.2729   1.0000
   6.750   0.7897   0.09441   0.08883  -0.0549   0.2510   1.0000
   7.000   0.7870   0.09818   0.09257  -0.0585   0.2340   1.0000
   7.250   0.7887   0.10232   0.09666  -0.0599   0.2190   1.0000
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