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NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il)
Reynolds number: 50,000
Max Cl/Cd: 25.67 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20710-il-50000-n5.txt
Download as CSV file: xf-sc20710-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0710 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5960   0.09734   0.08921  -0.0385   1.0000   0.0618
 -11.000  -0.6084   0.09043   0.08234  -0.0422   1.0000   0.0616
 -10.750  -0.6262   0.08396   0.07592  -0.0456   1.0000   0.0613
 -10.500  -0.6481   0.07839   0.07037  -0.0477   1.0000   0.0608
 -10.250  -0.6729   0.07382   0.06580  -0.0482   1.0000   0.0604
 -10.000  -0.6935   0.06895   0.06085  -0.0497   1.0000   0.0602
  -9.750  -0.7078   0.06428   0.05598  -0.0509   1.0000   0.0604
  -9.500  -0.7156   0.05971   0.05109  -0.0519   1.0000   0.0610
  -9.250  -0.7165   0.05519   0.04613  -0.0529   1.0000   0.0619
  -9.000  -0.7101   0.05081   0.04119  -0.0540   1.0000   0.0629
  -8.750  -0.6965   0.04740   0.03752  -0.0543   1.0000   0.0639
  -8.500  -0.6798   0.04466   0.03456  -0.0544   1.0000   0.0654
  -8.250  -0.6611   0.04244   0.03215  -0.0545   1.0000   0.0682
  -8.000  -0.6404   0.03994   0.02926  -0.0549   1.0000   0.0718
  -7.750  -0.6173   0.03735   0.02608  -0.0552   1.0000   0.0750
  -7.500  -0.5959   0.03543   0.02411  -0.0549   1.0000   0.0782
  -7.250  -0.5733   0.03393   0.02248  -0.0545   1.0000   0.0832
  -7.000  -0.5497   0.03234   0.02054  -0.0538   1.0000   0.0879
  -6.750  -0.5282   0.03102   0.01927  -0.0528   1.0000   0.0931
  -6.500  -0.5057   0.02994   0.01803  -0.0518   1.0000   0.1000
  -6.250  -0.4847   0.02889   0.01694  -0.0501   1.0000   0.1058
  -6.000  -0.4627   0.02800   0.01602  -0.0489   1.0000   0.1150
  -5.750  -0.4407   0.02707   0.01514  -0.0479   1.0000   0.1245
  -5.500  -0.4173   0.02615   0.01421  -0.0474   1.0000   0.1373
  -5.250  -0.3921   0.02515   0.01333  -0.0476   1.0000   0.1570
  -5.000  -0.3647   0.02396   0.01240  -0.0486   1.0000   0.1910
  -4.750  -0.3306   0.02209   0.01140  -0.0521   1.0000   0.2971
  -4.500  -0.3193   0.02168   0.01234  -0.0474   1.0000   0.4830
  -4.000  -0.2855   0.02305   0.01370  -0.0403   1.0000   0.6415
  -3.750  -0.2670   0.02375   0.01427  -0.0373   1.0000   0.6791
  -3.500  -0.2539   0.02442   0.01485  -0.0329   1.0000   0.7071
  -3.250  -0.2434   0.02499   0.01537  -0.0278   1.0000   0.7336
  -3.000  -0.2304   0.02538   0.01569  -0.0236   1.0000   0.7603
  -2.750  -0.2199   0.02551   0.01577  -0.0189   1.0000   0.7815
  -2.500  -0.2035   0.02545   0.01561  -0.0161   1.0000   0.7993
  -2.250  -0.1840   0.02527   0.01535  -0.0144   1.0000   0.8128
  -2.000  -0.1617   0.02507   0.01506  -0.0136   1.0000   0.8243
  -1.750  -0.1367   0.02491   0.01481  -0.0136   1.0000   0.8344
  -1.500  -0.1150   0.02466   0.01450  -0.0128   1.0000   0.8424
  -1.250  -0.0871   0.02457   0.01435  -0.0136   1.0000   0.8504
  -1.000  -0.0646   0.02435   0.01410  -0.0130   1.0000   0.8571
  -0.750  -0.0366   0.02430   0.01402  -0.0139   1.0000   0.8637
  -0.500  -0.0120   0.02417   0.01390  -0.0139   1.0000   0.8693
  -0.250   0.0147   0.02414   0.01387  -0.0144   1.0000   0.8748
   0.000   0.0436   0.02420   0.01396  -0.0156   1.0000   0.8797
   0.250   0.0684   0.02418   0.01399  -0.0158   1.0000   0.8845
   0.500   0.0957   0.02427   0.01414  -0.0166   1.0000   0.8892
   0.750   0.1242   0.02444   0.01440  -0.0178   1.0000   0.8939
   1.000   0.1490   0.02454   0.01460  -0.0181   1.0000   0.8985
   1.250   0.1754   0.02475   0.01493  -0.0189   1.0000   0.9035
   1.500   0.2078   0.02507   0.01540  -0.0209   0.9967   0.9078
   1.750   0.2566   0.02538   0.01590  -0.0258   0.9815   0.9110
   2.000   0.3103   0.02549   0.01624  -0.0311   0.9602   0.9136
   2.250   0.3699   0.02492   0.01595  -0.0362   0.9235   0.9159
   2.500   0.4255   0.02351   0.01482  -0.0388   0.8704   0.9182
   2.750   0.4552   0.02253   0.01410  -0.0373   0.8121   0.9219
   3.000   0.5321   0.02073   0.01160  -0.0403   0.5419   0.9227
   3.250   0.5463   0.02257   0.01189  -0.0375   0.3018   0.9269
   3.500   0.5653   0.02413   0.01272  -0.0367   0.2022   0.9314
   3.750   0.5902   0.02530   0.01361  -0.0366   0.1614   0.9358
   4.000   0.6162   0.02633   0.01449  -0.0367   0.1401   0.9401
   4.250   0.6456   0.02734   0.01551  -0.0372   0.1238   0.9444
   4.500   0.6776   0.02844   0.01667  -0.0380   0.1123   0.9488
   4.750   0.7102   0.02957   0.01793  -0.0388   0.1022   0.9539
   5.000   0.7428   0.03101   0.01934  -0.0398   0.0950   0.9595
   5.250   0.7750   0.03242   0.02104  -0.0405   0.0877   0.9658
   5.750   0.8366   0.03611   0.02518  -0.0421   0.0773   0.9896
   6.000   0.8658   0.03801   0.02728  -0.0429   0.0723   1.0000
   6.250   0.8936   0.04054   0.02993  -0.0438   0.0694   1.0000
   6.500   0.9173   0.04348   0.03355  -0.0435   0.0666   1.0000
   6.750   0.9381   0.04637   0.03695  -0.0432   0.0635   1.0000
   7.000   0.9579   0.04913   0.04003  -0.0431   0.0610   1.0000
   7.250   0.9758   0.05226   0.04350  -0.0428   0.0597   1.0000
   7.500   0.9907   0.05574   0.04729  -0.0424   0.0587   1.0000
   7.750   1.0021   0.05964   0.05145  -0.0419   0.0579   1.0000
   8.000   1.0023   0.06414   0.05655  -0.0403   0.0573   1.0000
   8.250   0.9975   0.06885   0.06176  -0.0388   0.0568   1.0000
   8.500   0.9871   0.07376   0.06708  -0.0376   0.0563   1.0000
   8.750   0.9717   0.07871   0.07235  -0.0367   0.0561   1.0000
   9.000   0.9529   0.08367   0.07754  -0.0362   0.0562   1.0000
   9.250   0.9323   0.08946   0.08351  -0.0375   0.0564   1.0000
   9.500   0.9131   0.09607   0.09025  -0.0408   0.0567   1.0000
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