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NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il)
Reynolds number: 500,000
Max Cl/Cd: 52.04 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20010-il-500000.txt
Download as CSV file: xf-sc20010-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -1.0785   0.04676   0.04311  -0.0260   1.0000   0.0200
 -12.000  -1.0927   0.04361   0.03974  -0.0237   1.0000   0.0201
 -11.750  -1.0981   0.04142   0.03739  -0.0210   1.0000   0.0202
 -11.500  -1.0933   0.03961   0.03544  -0.0193   1.0000   0.0205
 -11.250  -1.0879   0.03752   0.03317  -0.0175   1.0000   0.0208
 -11.000  -1.0825   0.03502   0.03041  -0.0157   1.0000   0.0210
 -10.750  -1.0751   0.03238   0.02747  -0.0139   1.0000   0.0212
 -10.500  -1.0634   0.03011   0.02492  -0.0124   1.0000   0.0214
 -10.250  -1.0485   0.02815   0.02271  -0.0111   1.0000   0.0217
 -10.000  -1.0314   0.02642   0.02076  -0.0100   1.0000   0.0220
  -9.750  -1.0124   0.02490   0.01903  -0.0090   1.0000   0.0223
  -9.500  -0.9921   0.02357   0.01752  -0.0082   1.0000   0.0227
  -9.250  -0.9705   0.02244   0.01622  -0.0074   1.0000   0.0230
  -9.000  -0.9482   0.02143   0.01507  -0.0067   1.0000   0.0233
  -8.750  -0.9285   0.01968   0.01321  -0.0058   1.0000   0.0241
  -8.500  -0.9054   0.01892   0.01244  -0.0053   1.0000   0.0248
  -8.250  -0.8815   0.01829   0.01177  -0.0049   1.0000   0.0256
  -8.000  -0.8576   0.01760   0.01102  -0.0043   1.0000   0.0265
  -7.750  -0.8336   0.01690   0.01025  -0.0038   1.0000   0.0273
  -7.500  -0.8090   0.01632   0.00958  -0.0033   1.0000   0.0281
  -7.250  -0.7870   0.01529   0.00854  -0.0025   1.0000   0.0295
  -7.000  -0.7623   0.01480   0.00806  -0.0021   1.0000   0.0310
  -6.750  -0.7372   0.01436   0.00759  -0.0017   1.0000   0.0330
  -6.500  -0.7135   0.01371   0.00691  -0.0011   1.0000   0.0354
  -6.250  -0.6882   0.01337   0.00660  -0.0007   1.0000   0.0385
  -6.000  -0.6637   0.01293   0.00614  -0.0002   1.0000   0.0423
  -5.750  -0.6390   0.01260   0.00585   0.0003   1.0000   0.0463
  -5.500  -0.6147   0.01231   0.00554   0.0009   1.0000   0.0499
  -5.250  -0.5924   0.01187   0.00515   0.0018   1.0000   0.0544
  -5.000  -0.5701   0.01167   0.00494   0.0028   1.0000   0.0580
  -4.750  -0.5416   0.01125   0.00455   0.0023   0.9977   0.0631
  -4.500  -0.5039   0.01096   0.00427   0.0000   0.9939   0.0690
  -4.250  -0.4679   0.01056   0.00392  -0.0020   0.9876   0.0772
  -4.000  -0.4319   0.01023   0.00362  -0.0039   0.9805   0.0871
  -3.750  -0.3974   0.00985   0.00334  -0.0055   0.9714   0.1034
  -3.500  -0.3663   0.00942   0.00307  -0.0064   0.9591   0.1374
  -3.250  -0.3391   0.00886   0.00282  -0.0065   0.9450   0.2081
  -3.000  -0.3150   0.00821   0.00257  -0.0060   0.9308   0.3097
  -2.750  -0.2932   0.00734   0.00230  -0.0052   0.9176   0.4644
  -2.500  -0.2720   0.00667   0.00224  -0.0038   0.9059   0.6249
  -2.250  -0.2457   0.00661   0.00226  -0.0033   0.8945   0.6746
  -2.000  -0.2188   0.00660   0.00225  -0.0029   0.8855   0.7013
  -1.750  -0.1913   0.00660   0.00224  -0.0026   0.8772   0.7208
  -1.500  -0.1637   0.00660   0.00224  -0.0023   0.8702   0.7353
  -1.250  -0.1359   0.00658   0.00224  -0.0021   0.8622   0.7488
  -1.000  -0.1086   0.00660   0.00223  -0.0017   0.8545   0.7614
  -0.750  -0.0815   0.00659   0.00224  -0.0013   0.8441   0.7769
  -0.500  -0.0547   0.00660   0.00226  -0.0007   0.8343   0.7932
  -0.250  -0.0269   0.00662   0.00226  -0.0005   0.8263   0.8044
   0.000   0.0000   0.00660   0.00228   0.0000   0.8158   0.8158
   0.250   0.0269   0.00662   0.00227   0.0005   0.8045   0.8264
   0.500   0.0547   0.00660   0.00226   0.0008   0.7930   0.8344
   0.750   0.0815   0.00659   0.00224   0.0013   0.7771   0.8441
   1.000   0.1086   0.00660   0.00223   0.0017   0.7614   0.8545
   1.250   0.1359   0.00658   0.00224   0.0021   0.7487   0.8623
   1.500   0.1637   0.00660   0.00224   0.0023   0.7353   0.8702
   1.750   0.1912   0.00660   0.00224   0.0026   0.7208   0.8772
   2.000   0.2187   0.00660   0.00225   0.0029   0.7014   0.8855
   2.250   0.2457   0.00661   0.00226   0.0033   0.6746   0.8945
   2.500   0.2719   0.00667   0.00224   0.0039   0.6249   0.9059
   2.750   0.2932   0.00734   0.00230   0.0052   0.4640   0.9176
   3.000   0.3150   0.00821   0.00257   0.0060   0.3096   0.9308
   3.250   0.3391   0.00886   0.00282   0.0065   0.2082   0.9451
   3.500   0.3663   0.00942   0.00307   0.0064   0.1374   0.9591
   3.750   0.3974   0.00985   0.00334   0.0055   0.1033   0.9715
   4.000   0.4320   0.01023   0.00362   0.0039   0.0871   0.9806
   4.250   0.4680   0.01056   0.00392   0.0020   0.0772   0.9876
   4.500   0.5040   0.01096   0.00427   0.0000   0.0690   0.9939
   4.750   0.5417   0.01125   0.00455  -0.0023   0.0631   0.9978
   5.000   0.5700   0.01167   0.00494  -0.0028   0.0580   1.0000
   5.250   0.5924   0.01187   0.00515  -0.0018   0.0544   1.0000
   5.500   0.6147   0.01231   0.00553  -0.0009   0.0499   1.0000
   5.750   0.6390   0.01260   0.00585  -0.0003   0.0463   1.0000
   6.000   0.6637   0.01293   0.00614   0.0002   0.0423   1.0000
   6.250   0.6882   0.01337   0.00660   0.0007   0.0386   1.0000
   6.500   0.7135   0.01371   0.00691   0.0011   0.0354   1.0000
   6.750   0.7372   0.01436   0.00758   0.0017   0.0329   1.0000
   7.000   0.7623   0.01480   0.00806   0.0021   0.0310   1.0000
   7.250   0.7870   0.01529   0.00854   0.0025   0.0295   1.0000
   7.500   0.8090   0.01632   0.00958   0.0033   0.0281   1.0000
   7.750   0.8336   0.01690   0.01025   0.0038   0.0273   1.0000
   8.000   0.8576   0.01760   0.01102   0.0043   0.0265   1.0000
   8.250   0.8815   0.01830   0.01178   0.0049   0.0256   1.0000
   8.500   0.9054   0.01892   0.01244   0.0053   0.0248   1.0000
   8.750   0.9285   0.01967   0.01321   0.0058   0.0241   1.0000
   9.000   0.9482   0.02144   0.01507   0.0067   0.0233   1.0000
   9.250   0.9706   0.02244   0.01622   0.0074   0.0230   1.0000
   9.500   0.9921   0.02357   0.01752   0.0082   0.0227   1.0000
   9.750   1.0125   0.02490   0.01903   0.0090   0.0223   1.0000
  10.000   1.0314   0.02642   0.02076   0.0100   0.0220   1.0000
  10.250   1.0486   0.02815   0.02271   0.0111   0.0217   1.0000
  10.500   1.0635   0.03012   0.02493   0.0124   0.0214   1.0000
  10.750   1.0752   0.03238   0.02747   0.0139   0.0212   1.0000
  11.000   1.0828   0.03501   0.03040   0.0157   0.0210   1.0000
  11.250   1.0884   0.03748   0.03313   0.0175   0.0207   1.0000
  11.500   1.0944   0.03950   0.03532   0.0192   0.0205   1.0000
  11.750   1.0987   0.04140   0.03736   0.0209   0.0202   1.0000
  12.000   1.0929   0.04365   0.03978   0.0237   0.0201   1.0000
  12.250   1.0809   0.04657   0.04290   0.0259   0.0200   1.0000
  12.500   0.6810   0.09468   0.09239   0.0075   0.0240   1.0000
  12.750   0.6841   0.09713   0.09482   0.0065   0.0237   1.0000
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