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NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il)
Reynolds number: 100,000
Max Cl/Cd: 27.43 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20714-il-100000.txt
Download as CSV file: xf-sc20714-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0714 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6453   0.09096   0.08500  -0.0551   1.0000   0.1158
 -11.500  -0.7461   0.07622   0.07006  -0.0586   1.0000   0.1021
 -11.250  -0.7616   0.07243   0.06627  -0.0568   1.0000   0.1010
 -11.000  -0.7922   0.06908   0.06288  -0.0537   1.0000   0.1000
 -10.750  -0.8216   0.06474   0.05843  -0.0523   1.0000   0.0987
 -10.500  -0.8457   0.05988   0.05330  -0.0518   1.0000   0.0974
 -10.250  -0.8564   0.05552   0.04862  -0.0514   1.0000   0.0971
 -10.000  -0.8569   0.05164   0.04442  -0.0514   1.0000   0.0975
  -9.750  -0.8503   0.04806   0.04047  -0.0516   1.0000   0.0984
  -9.500  -0.8382   0.04467   0.03668  -0.0520   1.0000   0.0993
  -9.250  -0.8215   0.04158   0.03316  -0.0526   1.0000   0.1004
  -9.000  -0.8009   0.03902   0.03013  -0.0534   1.0000   0.1022
  -8.750  -0.7798   0.03657   0.02746  -0.0537   1.0000   0.1047
  -8.500  -0.7584   0.03509   0.02599  -0.0534   1.0000   0.1076
  -8.250  -0.7353   0.03362   0.02438  -0.0533   1.0000   0.1106
  -8.000  -0.7105   0.03218   0.02267  -0.0534   1.0000   0.1141
  -7.750  -0.6861   0.03070   0.02104  -0.0535   1.0000   0.1180
  -7.500  -0.6628   0.02965   0.02005  -0.0531   1.0000   0.1224
  -7.250  -0.6379   0.02870   0.01899  -0.0529   1.0000   0.1274
  -7.000  -0.6137   0.02764   0.01790  -0.0524   1.0000   0.1329
  -6.750  -0.5901   0.02683   0.01719  -0.0519   1.0000   0.1392
  -6.500  -0.5647   0.02608   0.01633  -0.0517   1.0000   0.1467
  -6.250  -0.5418   0.02528   0.01576  -0.0509   1.0000   0.1554
  -6.000  -0.5176   0.02456   0.01513  -0.0504   1.0000   0.1658
  -5.750  -0.4924   0.02392   0.01462  -0.0502   1.0000   0.1805
  -5.500  -0.4664   0.02321   0.01419  -0.0502   1.0000   0.2008
  -5.250  -0.4364   0.02235   0.01374  -0.0513   1.0000   0.2410
  -5.000  -0.4045   0.02114   0.01457  -0.0527   1.0000   0.4733
  -4.750  -0.3999   0.02290   0.01658  -0.0455   1.0000   0.5681
  -4.500  -0.3824   0.02432   0.01790  -0.0422   1.0000   0.6055
  -4.250  -0.3713   0.02570   0.01924  -0.0372   1.0000   0.6245
  -4.000  -0.3599   0.02693   0.02043  -0.0324   1.0000   0.6404
  -3.750  -0.3462   0.02796   0.02139  -0.0285   1.0000   0.6557
  -3.500  -0.3294   0.02882   0.02220  -0.0256   1.0000   0.6715
  -3.250  -0.3266   0.02972   0.02312  -0.0186   1.0000   0.6788
  -3.000  -0.3116   0.03038   0.02375  -0.0154   1.0000   0.6934
  -2.750  -0.2929   0.03101   0.02432  -0.0134   1.0000   0.7097
  -2.500  -0.2910   0.03143   0.02478  -0.0066   1.0000   0.7178
  -2.250  -0.2751   0.03179   0.02511  -0.0040   1.0000   0.7324
  -1.750  -0.2520   0.03241   0.02572   0.0034   1.0000   0.7625
  -1.500  -0.2411   0.03272   0.02604   0.0073   1.0000   0.7820
  -1.250  -0.2347   0.03272   0.02605   0.0122   1.0000   0.8004
  -1.000  -0.2216   0.03269   0.02602   0.0149   1.0000   0.8161
  -0.750  -0.2123   0.03218   0.02552   0.0184   1.0000   0.8251
  -0.500  -0.1834   0.03233   0.02564   0.0163   1.0000   0.8326
  -0.250  -0.1686   0.03197   0.02528   0.0181   1.0000   0.8386
   0.000  -0.1280   0.03230   0.02559   0.0141   0.9946   0.8448
   0.250  -0.0803   0.03256   0.02585   0.0092   0.9841   0.8499
   0.500  -0.0384   0.03264   0.02594   0.0057   0.9729   0.8542
   0.750   0.0065   0.03284   0.02615   0.0013   0.9615   0.8583
   1.000   0.0574   0.03310   0.02643  -0.0042   0.9493   0.8616
   1.250   0.1053   0.03291   0.02628  -0.0083   0.9351   0.8647
   1.500   0.1547   0.03249   0.02591  -0.0123   0.9194   0.8677
   1.750   0.2056   0.03179   0.02529  -0.0161   0.9008   0.8706
   2.000   0.2602   0.03078   0.02435  -0.0201   0.8810   0.8732
   2.250   0.3148   0.02965   0.02331  -0.0239   0.8629   0.8757
   2.500   0.3650   0.02833   0.02210  -0.0266   0.8454   0.8781
   2.750   0.4088   0.02666   0.02056  -0.0276   0.8264   0.8806
   3.000   0.4535   0.02496   0.01898  -0.0286   0.8063   0.8823
   3.250   0.4928   0.02341   0.01756  -0.0288   0.7772   0.8833
   3.500   0.5320   0.02196   0.01615  -0.0287   0.7222   0.8845
   3.750   0.5977   0.02179   0.01420  -0.0322   0.4061   0.8865
   4.000   0.6065   0.02351   0.01484  -0.0296   0.2659   0.8878
   4.250   0.6280   0.02467   0.01554  -0.0292   0.2160   0.8887
   4.500   0.6544   0.02571   0.01627  -0.0297   0.1908   0.8894
   4.750   0.6852   0.02671   0.01711  -0.0308   0.1734   0.8902
   5.000   0.7188   0.02781   0.01800  -0.0325   0.1598   0.8911
   5.250   0.7499   0.02855   0.01881  -0.0334   0.1501   0.8926
   5.500   0.7823   0.02966   0.01978  -0.0346   0.1420   0.8944
   5.750   0.8126   0.03048   0.02072  -0.0353   0.1346   0.8958
   6.000   0.8485   0.03202   0.02207  -0.0374   0.1280   0.8969
   6.250   0.8777   0.03296   0.02329  -0.0379   0.1225   0.8980
   6.500   0.9084   0.03412   0.02448  -0.0389   0.1173   0.8991
   6.750   0.9398   0.03594   0.02635  -0.0402   0.1128   0.9003
   7.000   0.9666   0.03746   0.02824  -0.0404   0.1091   0.9017
   7.250   0.9946   0.03899   0.02990  -0.0409   0.1053   0.9035
   7.500   1.0249   0.04110   0.03195  -0.0424   0.1017   0.9053
   7.750   1.0429   0.04326   0.03457  -0.0412   0.0996   0.9068
   8.000   1.0593   0.04571   0.03750  -0.0398   0.0981   0.9081
   8.250   1.0731   0.04844   0.04068  -0.0383   0.0966   0.9093
   8.500   1.0846   0.05122   0.04385  -0.0367   0.0951   0.9105
   8.750   1.0956   0.05395   0.04689  -0.0353   0.0934   0.9119
   9.000   1.1037   0.05709   0.05034  -0.0338   0.0925   0.9132
   9.250   1.0918   0.06210   0.05593  -0.0303   0.0938   0.9143
   9.500   1.0713   0.06752   0.06186  -0.0267   0.0958   0.9154
   9.750   1.0502   0.07233   0.06700  -0.0235   0.0976   0.9167
  10.000   1.0366   0.07724   0.07211  -0.0219   0.0992   0.9182
  10.250   1.0451   0.08231   0.07723  -0.0222   0.1005   0.9198
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