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NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il)
Reynolds number: 100,000
Max Cl/Cd: 31.92 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20612-il-100000-n5.txt
Download as CSV file: xf-sc20612-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0612 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6974   0.09217   0.08596  -0.0448   1.0000   0.0434
 -13.000  -0.7531   0.07729   0.07090  -0.0552   1.0000   0.0429
 -12.750  -0.7912   0.06875   0.06215  -0.0602   1.0000   0.0427
 -12.500  -0.8214   0.06263   0.05581  -0.0625   1.0000   0.0427
 -12.250  -0.8472   0.05788   0.05082  -0.0630   1.0000   0.0428
 -12.000  -0.8705   0.05418   0.04690  -0.0617   1.0000   0.0430
 -11.750  -0.8912   0.05104   0.04353  -0.0596   1.0000   0.0432
 -11.500  -0.9045   0.04759   0.03970  -0.0586   1.0000   0.0437
 -11.250  -0.8993   0.04571   0.03775  -0.0575   1.0000   0.0444
 -11.000  -0.8906   0.04426   0.03625  -0.0565   1.0000   0.0452
 -10.750  -0.8819   0.04263   0.03450  -0.0556   1.0000   0.0463
 -10.500  -0.8725   0.04076   0.03242  -0.0546   1.0000   0.0476
 -10.250  -0.8620   0.03861   0.02996  -0.0538   1.0000   0.0490
 -10.000  -0.8492   0.03639   0.02735  -0.0529   1.0000   0.0504
  -9.750  -0.8330   0.03479   0.02564  -0.0521   1.0000   0.0516
  -9.500  -0.8155   0.03368   0.02452  -0.0513   1.0000   0.0531
  -9.250  -0.7973   0.03255   0.02328  -0.0507   1.0000   0.0552
  -9.000  -0.7783   0.03125   0.02175  -0.0500   1.0000   0.0576
  -8.750  -0.7589   0.02999   0.02037  -0.0492   1.0000   0.0597
  -8.500  -0.7390   0.02901   0.01942  -0.0485   1.0000   0.0617
  -8.250  -0.7183   0.02811   0.01844  -0.0479   1.0000   0.0646
  -8.000  -0.6968   0.02722   0.01734  -0.0473   1.0000   0.0681
  -7.750  -0.6759   0.02631   0.01654  -0.0467   1.0000   0.0709
  -7.500  -0.6540   0.02556   0.01577  -0.0462   1.0000   0.0744
  -7.250  -0.6313   0.02488   0.01493  -0.0457   1.0000   0.0787
  -7.000  -0.6089   0.02410   0.01426  -0.0455   1.0000   0.0826
  -6.750  -0.5854   0.02350   0.01364  -0.0453   1.0000   0.0878
  -6.500  -0.5616   0.02285   0.01298  -0.0451   1.0000   0.0929
  -6.250  -0.5370   0.02228   0.01245  -0.0452   1.0000   0.0990
  -6.000  -0.5118   0.02173   0.01190  -0.0453   1.0000   0.1055
  -5.750  -0.4856   0.02118   0.01141  -0.0457   1.0000   0.1135
  -5.500  -0.4585   0.02065   0.01093  -0.0463   1.0000   0.1228
  -5.250  -0.4307   0.02016   0.01050  -0.0470   1.0000   0.1351
  -5.000  -0.4017   0.01964   0.01012  -0.0480   1.0000   0.1540
  -4.750  -0.3711   0.01906   0.00973  -0.0495   1.0000   0.1865
  -4.500  -0.3362   0.01821   0.00934  -0.0523   1.0000   0.2617
  -4.250  -0.2967   0.01711   0.00919  -0.0563   1.0000   0.4251
  -4.000  -0.2807   0.01750   0.01014  -0.0530   1.0000   0.5286
  -3.750  -0.2580   0.01790   0.01061  -0.0517   0.9998   0.5781
  -3.500  -0.2248   0.01829   0.01093  -0.0527   0.9965   0.6116
  -3.250  -0.1895   0.01872   0.01127  -0.0541   0.9936   0.6381
  -3.000  -0.1609   0.01923   0.01175  -0.0538   0.9893   0.6554
  -2.750  -0.1322   0.01983   0.01234  -0.0534   0.9852   0.6722
  -2.500  -0.1032   0.02049   0.01299  -0.0528   0.9813   0.6891
  -2.250  -0.0852   0.02114   0.01370  -0.0495   0.9752   0.6988
  -2.000  -0.0537   0.02146   0.01398  -0.0500   0.9717   0.7103
  -1.750  -0.0258   0.02169   0.01421  -0.0497   0.9680   0.7158
  -1.500   0.0052   0.02175   0.01424  -0.0507   0.9632   0.7225
  -1.250   0.0399   0.02181   0.01428  -0.0523   0.9592   0.7285
  -1.000   0.0730   0.02191   0.01440  -0.0532   0.9557   0.7325
  -0.750   0.1008   0.02192   0.01442  -0.0533   0.9487   0.7365
  -0.500   0.1388   0.02187   0.01438  -0.0558   0.9441   0.7406
  -0.250   0.1805   0.02176   0.01428  -0.0591   0.9389   0.7453
   0.000   0.2119   0.02166   0.01424  -0.0596   0.9305   0.7475
   0.250   0.2498   0.02148   0.01411  -0.0614   0.9231   0.7497
   0.500   0.2893   0.02117   0.01386  -0.0634   0.9132   0.7519
   0.750   0.3382   0.02040   0.01315  -0.0663   0.8969   0.7541
   1.000   0.3792   0.01968   0.01249  -0.0678   0.8765   0.7570
   1.250   0.4167   0.01911   0.01198  -0.0689   0.8536   0.7603
   1.500   0.4543   0.01859   0.01149  -0.0700   0.8239   0.7635
   1.750   0.4864   0.01817   0.01110  -0.0697   0.7860   0.7654
   2.000   0.5225   0.01778   0.01060  -0.0700   0.7177   0.7675
   2.250   0.5570   0.01802   0.01002  -0.0698   0.5428   0.7694
   2.500   0.5755   0.01914   0.01025  -0.0681   0.3842   0.7718
   2.750   0.5971   0.02011   0.01064  -0.0674   0.2727   0.7744
   3.000   0.6221   0.02094   0.01104  -0.0674   0.2027   0.7774
   3.250   0.6491   0.02163   0.01148  -0.0678   0.1630   0.7806
   3.500   0.6715   0.02220   0.01193  -0.0668   0.1424   0.7827
   3.750   0.6949   0.02274   0.01244  -0.0660   0.1284   0.7850
   4.000   0.7192   0.02330   0.01298  -0.0654   0.1176   0.7876
   4.250   0.7435   0.02398   0.01358  -0.0650   0.1095   0.7905
   4.500   0.7703   0.02453   0.01420  -0.0651   0.1015   0.7934
   4.750   0.7971   0.02528   0.01488  -0.0653   0.0953   0.7962
   5.000   0.8225   0.02586   0.01553  -0.0650   0.0890   0.7983
   5.250   0.8452   0.02658   0.01621  -0.0642   0.0842   0.8005
   5.500   0.8699   0.02728   0.01702  -0.0637   0.0794   0.8031
   5.750   0.8947   0.02803   0.01780  -0.0634   0.0751   0.8060
   6.000   0.9203   0.02897   0.01871  -0.0633   0.0714   0.8089
   6.250   0.9477   0.02986   0.01977  -0.0635   0.0672   0.8117
   6.500   0.9736   0.03082   0.02074  -0.0635   0.0642   0.8142
   6.750   0.9970   0.03189   0.02184  -0.0629   0.0616   0.8164
   7.000   1.0208   0.03296   0.02316  -0.0622   0.0585   0.8189
   7.250   1.0441   0.03398   0.02427  -0.0617   0.0560   0.8219
   7.500   1.0683   0.03519   0.02548  -0.0615   0.0542   0.8252
   7.750   1.0927   0.03690   0.02746  -0.0613   0.0523   0.8283
   8.000   1.1143   0.03849   0.02936  -0.0606   0.0501   0.8310
   8.250   1.1335   0.03974   0.03078  -0.0595   0.0483   0.8335
   8.500   1.1529   0.04093   0.03203  -0.0586   0.0470   0.8365
   8.750   1.1708   0.04285   0.03417  -0.0576   0.0459   0.8398
   9.000   1.1837   0.04564   0.03747  -0.0560   0.0447   0.8431
   9.250   1.1939   0.04845   0.04073  -0.0542   0.0436   0.8462
   9.500   1.2002   0.05093   0.04355  -0.0518   0.0427   0.8490
   9.750   1.2068   0.05309   0.04597  -0.0497   0.0418   0.8519
  10.000   1.2136   0.05503   0.04809  -0.0478   0.0410   0.8551
  10.250   1.2215   0.05679   0.04996  -0.0462   0.0403   0.8584
  10.500   1.2205   0.05928   0.05264  -0.0438   0.0397   0.8616
  10.750   1.1963   0.06314   0.05696  -0.0393   0.0394   0.8645
  11.000   1.1706   0.06773   0.06196  -0.0363   0.0392   0.8675
  11.250   1.1421   0.07312   0.06770  -0.0350   0.0391   0.8705
  11.500   1.1100   0.07970   0.07459  -0.0358   0.0392   0.8733
  11.750   1.0741   0.08815   0.08332  -0.0397   0.0393   0.8756
  12.000   1.0331   0.09974   0.09516  -0.0476   0.0396   0.8771
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