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NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il)
Reynolds number: 100,000
Max Cl/Cd: 31.74 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20606-il-100000.txt
Download as CSV file: xf-sc20606-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0606 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4937   0.09040   0.08555  -0.0131   1.0000   0.1056
  -9.250  -0.5067   0.08640   0.08163  -0.0162   1.0000   0.1095
  -9.000  -0.5320   0.08234   0.07768  -0.0213   1.0000   0.1106
  -8.750  -0.6051   0.08949   0.08454  -0.0106   1.0000   0.1030
  -8.500  -0.6076   0.08543   0.08054  -0.0143   1.0000   0.1076
  -8.250  -0.6237   0.07780   0.07275  -0.0339   1.0000   0.1113
  -8.000  -0.6034   0.07523   0.07039  -0.0238   1.0000   0.1158
  -7.750  -0.6057   0.06893   0.06380  -0.0364   1.0000   0.1254
  -7.500  -0.5908   0.06595   0.06103  -0.0308   1.0000   0.1300
  -7.250  -0.5816   0.06106   0.05600  -0.0354   1.0000   0.1416
  -7.000  -0.5682   0.05700   0.05183  -0.0378   1.0000   0.1552
  -6.750  -0.5535   0.05377   0.04855  -0.0377   1.0000   0.1713
  -6.500  -0.5385   0.05072   0.04546  -0.0383   1.0000   0.1983
  -6.250  -0.4674   0.03650   0.02875  -0.0530   1.0000   0.0833
  -6.000  -0.4354   0.03091   0.02257  -0.0541   1.0000   0.0689
  -5.750  -0.4058   0.02717   0.01846  -0.0549   1.0000   0.0659
  -5.500  -0.3755   0.02438   0.01521  -0.0552   1.0000   0.0649
  -5.250  -0.3461   0.02238   0.01281  -0.0550   1.0000   0.0677
  -5.000  -0.3185   0.02041   0.01072  -0.0550   1.0000   0.0742
  -4.750  -0.2910   0.01885   0.00906  -0.0545   1.0000   0.0807
  -4.500  -0.2633   0.01737   0.00760  -0.0544   1.0000   0.0955
  -4.250  -0.2336   0.01585   0.00627  -0.0549   1.0000   0.1237
  -4.000  -0.1986   0.01241   0.00552  -0.0574   1.0000   0.6201
  -3.750  -0.1842   0.01277   0.00599  -0.0526   1.0000   0.7214
  -3.500  -0.1694   0.01308   0.00624  -0.0483   1.0000   0.7678
  -3.250  -0.1601   0.01329   0.00642  -0.0427   1.0000   0.8027
  -3.000  -0.1506   0.01336   0.00645  -0.0374   1.0000   0.8346
  -2.750  -0.1447   0.01325   0.00633  -0.0313   1.0000   0.8673
  -2.500  -0.1416   0.01288   0.00596  -0.0247   1.0000   0.8996
  -2.250  -0.1342   0.01233   0.00537  -0.0196   1.0000   0.9332
  -2.000  -0.1158   0.01165   0.00463  -0.0172   1.0000   0.9673
  -1.750  -0.0795   0.01126   0.00414  -0.0193   1.0000   1.0000
  -1.500  -0.0501   0.01117   0.00396  -0.0208   1.0000   1.0000
  -1.250  -0.0181   0.01114   0.00385  -0.0228   1.0000   1.0000
  -1.000   0.0152   0.01115   0.00381  -0.0249   1.0000   1.0000
  -0.750   0.0489   0.01119   0.00381  -0.0271   1.0000   1.0000
  -0.500   0.0827   0.01126   0.00387  -0.0291   1.0000   1.0000
  -0.250   0.1163   0.01135   0.00397  -0.0311   1.0000   1.0000
   0.000   0.1497   0.01146   0.00413  -0.0330   1.0000   1.0000
   0.250   0.1826   0.01159   0.00433  -0.0347   1.0000   1.0000
   0.500   0.2150   0.01175   0.00456  -0.0363   1.0000   1.0000
   0.750   0.2469   0.01192   0.00485  -0.0378   1.0000   1.0000
   1.000   0.2784   0.01212   0.00522  -0.0392   1.0000   1.0000
   1.250   0.3092   0.01234   0.00561  -0.0404   1.0000   1.0000
   1.500   0.3396   0.01259   0.00606  -0.0415   1.0000   1.0000
   1.750   0.3694   0.01287   0.00660  -0.0425   1.0000   1.0000
   2.000   0.4786   0.01508   0.00585  -0.0535   0.1546   1.0000
   2.250   0.5042   0.01684   0.00723  -0.0532   0.1049   1.0000
   2.500   0.5322   0.01841   0.00873  -0.0530   0.0859   1.0000
   2.750   0.5617   0.02015   0.01041  -0.0531   0.0742   1.0000
   3.000   0.5928   0.02204   0.01244  -0.0532   0.0691   1.0000
   3.250   0.6233   0.02492   0.01537  -0.0535   0.0657   1.0000
   3.500   0.6534   0.02670   0.01767  -0.0532   0.0621   1.0000
   3.750   0.6827   0.02973   0.02112  -0.0528   0.0631   1.0000
   4.000   0.7109   0.03325   0.02493  -0.0524   0.0662   1.0000
   4.500   0.7867   0.04912   0.04399  -0.0507   0.2064   1.0000
   5.250   0.8308   0.05957   0.05486  -0.0496   0.1408   1.0000
   5.500   0.8434   0.06346   0.05890  -0.0497   0.1267   1.0000
   5.750   0.8608   0.06794   0.06320  -0.0486   0.1207   1.0000
   6.000   0.8652   0.07199   0.06771  -0.0505   0.1100   1.0000
   6.250   0.8843   0.07796   0.07334  -0.0488   0.1063   1.0000
   6.500   0.8743   0.08199   0.07800  -0.0538   0.0991   1.0000
   6.750   0.8841   0.08597   0.08198  -0.0530   0.0946   1.0000
   7.000   0.8976   0.09257   0.08840  -0.0511   0.0920   1.0000
   7.250   0.8778   0.09714   0.09329  -0.0589   0.0901   1.0000
   7.500   0.7305   0.09435   0.09070  -0.0515   0.1017   1.0000
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