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NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il)
Reynolds number: 50,000
Max Cl/Cd: 22.9 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20010-il-50000-n5.txt
Download as CSV file: xf-sc20010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0010 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7184   0.10294   0.09525  -0.0071   1.0000   0.0589
 -10.750  -0.7268   0.09599   0.08831  -0.0113   1.0000   0.0586
 -10.500  -0.7407   0.08910   0.08139  -0.0157   1.0000   0.0582
 -10.250  -0.7588   0.08272   0.07496  -0.0194   1.0000   0.0579
 -10.000  -0.7791   0.07724   0.06938  -0.0213   1.0000   0.0576
  -9.750  -0.7988   0.07254   0.06454  -0.0213   1.0000   0.0575
  -9.500  -0.8136   0.06780   0.05955  -0.0210   1.0000   0.0575
  -9.250  -0.8239   0.06319   0.05461  -0.0202   1.0000   0.0579
  -9.000  -0.8307   0.05868   0.04961  -0.0190   1.0000   0.0586
  -8.750  -0.8263   0.05513   0.04582  -0.0180   1.0000   0.0599
  -8.500  -0.8134   0.05270   0.04330  -0.0172   1.0000   0.0617
  -8.250  -0.8028   0.04974   0.04003  -0.0162   1.0000   0.0633
  -8.000  -0.7911   0.04652   0.03641  -0.0151   1.0000   0.0647
  -7.750  -0.7770   0.04344   0.03288  -0.0140   1.0000   0.0668
  -7.500  -0.7612   0.04057   0.02935  -0.0127   1.0000   0.0701
  -7.250  -0.7411   0.03848   0.02723  -0.0122   1.0000   0.0733
  -7.000  -0.7198   0.03649   0.02502  -0.0115   1.0000   0.0768
  -6.750  -0.6976   0.03454   0.02263  -0.0106   1.0000   0.0821
  -6.500  -0.6744   0.03281   0.02088  -0.0101   1.0000   0.0869
  -6.250  -0.6503   0.03132   0.01922  -0.0095   1.0000   0.0933
  -6.000  -0.6256   0.02985   0.01766  -0.0090   1.0000   0.1001
  -5.750  -0.6005   0.02863   0.01632  -0.0083   1.0000   0.1084
  -5.500  -0.5758   0.02743   0.01515  -0.0077   1.0000   0.1170
  -5.250  -0.5513   0.02636   0.01399  -0.0070   1.0000   0.1275
  -4.750  -0.5061   0.02437   0.01205  -0.0051   1.0000   0.1549
  -4.500  -0.4861   0.02332   0.01117  -0.0040   1.0000   0.1746
  -4.250  -0.4671   0.02223   0.01029  -0.0028   1.0000   0.2052
  -4.000  -0.4504   0.02094   0.00946  -0.0014   1.0000   0.2644
  -3.750  -0.4401   0.01937   0.00883   0.0012   1.0000   0.3979
  -3.500  -0.4285   0.01871   0.00942   0.0063   1.0000   0.6165
  -3.250  -0.4136   0.01878   0.00952   0.0099   1.0000   0.7116
  -3.000  -0.3963   0.01894   0.00967   0.0134   1.0000   0.7690
  -2.750  -0.3750   0.01924   0.00996   0.0165   1.0000   0.8166
  -2.500  -0.3474   0.01962   0.01025   0.0184   1.0000   0.8587
  -2.250  -0.2959   0.02025   0.01069   0.0164   1.0000   0.9028
  -2.000  -0.2235   0.02063   0.01080   0.0092   1.0000   0.9327
  -1.750  -0.1728   0.02055   0.01054   0.0046   1.0000   0.9485
  -1.500  -0.1324   0.02037   0.01026   0.0015   1.0000   0.9607
  -1.250  -0.0962   0.02020   0.01000  -0.0011   1.0000   0.9719
  -1.000  -0.0605   0.02002   0.00978  -0.0036   1.0000   0.9819
  -0.750  -0.0251   0.01987   0.00960  -0.0062   1.0000   0.9913
  -0.500   0.0066   0.01976   0.00948  -0.0083   1.0000   1.0000
  -0.250   0.0042   0.01977   0.00950  -0.0043   1.0000   1.0000
   0.000   0.0000   0.01977   0.00951   0.0000   1.0000   1.0000
   0.250  -0.0042   0.01976   0.00950   0.0043   1.0000   1.0000
   0.500  -0.0066   0.01976   0.00948   0.0083   1.0000   1.0000
   0.750   0.0251   0.01986   0.00959   0.0062   0.9913   1.0000
   1.000   0.0604   0.02002   0.00978   0.0036   0.9819   1.0000
   1.250   0.0962   0.02019   0.01000   0.0011   0.9719   1.0000
   1.500   0.1324   0.02037   0.01025  -0.0015   0.9607   1.0000
   1.750   0.1728   0.02055   0.01054  -0.0046   0.9485   1.0000
   2.000   0.2235   0.02063   0.01080  -0.0092   0.9327   1.0000
   2.250   0.2959   0.02025   0.01069  -0.0164   0.9028   1.0000
   2.500   0.3473   0.01961   0.01024  -0.0184   0.8587   1.0000
   2.750   0.3750   0.01924   0.00995  -0.0165   0.8167   1.0000
   3.000   0.3963   0.01894   0.00967  -0.0134   0.7691   1.0000
   3.250   0.4135   0.01878   0.00952  -0.0099   0.7116   1.0000
   3.500   0.4285   0.01871   0.00942  -0.0063   0.6165   1.0000
   3.750   0.4401   0.01937   0.00883  -0.0012   0.3980   1.0000
   4.000   0.4504   0.02094   0.00946   0.0014   0.2645   1.0000
   4.250   0.4671   0.02223   0.01029   0.0028   0.2052   1.0000
   4.500   0.4861   0.02332   0.01117   0.0040   0.1746   1.0000
   4.750   0.5061   0.02437   0.01205   0.0051   0.1549   1.0000
   5.250   0.5513   0.02636   0.01399   0.0070   0.1275   1.0000
   5.500   0.5758   0.02742   0.01515   0.0077   0.1170   1.0000
   5.750   0.6005   0.02863   0.01632   0.0083   0.1084   1.0000
   6.000   0.6256   0.02985   0.01766   0.0090   0.1001   1.0000
   6.250   0.6503   0.03132   0.01922   0.0095   0.0933   1.0000
   6.500   0.6744   0.03281   0.02088   0.0101   0.0869   1.0000
   6.750   0.6976   0.03454   0.02263   0.0106   0.0821   1.0000
   7.000   0.7198   0.03649   0.02502   0.0115   0.0768   1.0000
   7.250   0.7412   0.03848   0.02723   0.0122   0.0733   1.0000
   7.500   0.7612   0.04057   0.02935   0.0127   0.0701   1.0000
   7.750   0.7770   0.04344   0.03288   0.0140   0.0668   1.0000
   8.000   0.7911   0.04652   0.03641   0.0151   0.0648   1.0000
   8.250   0.8029   0.04974   0.04004   0.0162   0.0633   1.0000
   8.500   0.8136   0.05270   0.04330   0.0172   0.0616   1.0000
   8.750   0.8264   0.05514   0.04582   0.0180   0.0599   1.0000
   9.000   0.8308   0.05868   0.04962   0.0190   0.0586   1.0000
   9.250   0.8241   0.06321   0.05462   0.0201   0.0579   1.0000
   9.500   0.8137   0.06782   0.05957   0.0209   0.0575   1.0000
   9.750   0.7990   0.07257   0.06457   0.0212   0.0574   1.0000
  10.000   0.7794   0.07727   0.06942   0.0212   0.0576   1.0000
  10.250   0.7592   0.08277   0.07501   0.0193   0.0579   1.0000
  10.500   0.7411   0.08916   0.08146   0.0156   0.0582   1.0000
  10.750   0.7273   0.09607   0.08838   0.0112   0.0586   1.0000
  11.000   0.7190   0.10302   0.09534   0.0069   0.0589   1.0000
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