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NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63012A AIRFOIL (n63012a-il)
Reynolds number: 100,000
Max Cl/Cd: 38.28 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63012a-il-100000-n5.txt
Download as CSV file: xf-n63012a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63012A 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7603   0.09822   0.09295  -0.0120   1.0000   0.0279
 -12.500  -0.7822   0.08943   0.08408  -0.0179   1.0000   0.0277
 -12.250  -0.8050   0.08166   0.07619  -0.0231   1.0000   0.0275
 -12.000  -0.8271   0.07502   0.06940  -0.0271   1.0000   0.0274
 -11.750  -0.8480   0.06938   0.06356  -0.0297   1.0000   0.0273
 -11.500  -0.8675   0.06454   0.05852  -0.0311   1.0000   0.0273
 -11.250  -0.8850   0.06039   0.05413  -0.0312   1.0000   0.0273
 -11.000  -0.9004   0.05677   0.05025  -0.0300   1.0000   0.0273
 -10.750  -0.9134   0.05360   0.04677  -0.0278   1.0000   0.0275
 -10.500  -0.9216   0.05059   0.04337  -0.0254   1.0000   0.0279
 -10.250  -0.9217   0.04751   0.04004  -0.0237   1.0000   0.0285
 -10.000  -0.9145   0.04514   0.03752  -0.0224   1.0000   0.0292
  -9.750  -0.9054   0.04296   0.03514  -0.0211   1.0000   0.0300
  -9.500  -0.8946   0.04062   0.03253  -0.0197   1.0000   0.0306
  -9.250  -0.8814   0.03827   0.02989  -0.0183   1.0000   0.0311
  -9.000  -0.8656   0.03609   0.02743  -0.0171   1.0000   0.0318
  -8.750  -0.8477   0.03406   0.02515  -0.0160   1.0000   0.0327
  -8.500  -0.8281   0.03219   0.02302  -0.0150   1.0000   0.0336
  -8.250  -0.8076   0.03054   0.02115  -0.0141   1.0000   0.0349
  -8.000  -0.7870   0.02912   0.01954  -0.0131   1.0000   0.0366
  -7.750  -0.7681   0.02767   0.01813  -0.0122   1.0000   0.0387
  -7.500  -0.7486   0.02648   0.01691  -0.0112   1.0000   0.0407
  -7.250  -0.7295   0.02531   0.01564  -0.0099   1.0000   0.0429
  -7.000  -0.7112   0.02424   0.01446  -0.0085   1.0000   0.0453
  -6.750  -0.6953   0.02313   0.01335  -0.0068   1.0000   0.0484
  -6.500  -0.6785   0.02227   0.01249  -0.0052   1.0000   0.0533
  -6.250  -0.6625   0.02139   0.01156  -0.0034   1.0000   0.0589
  -6.000  -0.6469   0.02055   0.01071  -0.0016   1.0000   0.0666
  -5.750  -0.6318   0.01972   0.00993   0.0004   1.0000   0.0782
  -5.500  -0.6168   0.01890   0.00920   0.0023   1.0000   0.0967
  -5.250  -0.6033   0.01794   0.00850   0.0043   1.0000   0.1319
  -5.000  -0.5916   0.01683   0.00781   0.0064   1.0000   0.2034
  -4.750  -0.5818   0.01562   0.00728   0.0088   1.0000   0.3197
  -4.500  -0.5695   0.01488   0.00710   0.0112   1.0000   0.4328
  -4.250  -0.5360   0.01454   0.00704   0.0098   0.9911   0.5208
  -4.000  -0.5013   0.01444   0.00702   0.0084   0.9824   0.5747
  -3.750  -0.4658   0.01443   0.00704   0.0070   0.9740   0.6165
  -3.500  -0.4320   0.01446   0.00709   0.0060   0.9646   0.6494
  -3.250  -0.3981   0.01449   0.00706   0.0050   0.9555   0.6755
  -3.000  -0.3624   0.01451   0.00702   0.0037   0.9474   0.6947
  -2.750  -0.3307   0.01447   0.00693   0.0030   0.9367   0.7098
  -2.500  -0.2976   0.01441   0.00678   0.0020   0.9271   0.7225
  -2.250  -0.2642   0.01433   0.00661   0.0010   0.9179   0.7344
  -2.000  -0.2336   0.01428   0.00652   0.0006   0.9070   0.7441
  -1.750  -0.2026   0.01422   0.00640   0.0001   0.8970   0.7544
  -1.500  -0.1718   0.01414   0.00626  -0.0004   0.8874   0.7654
  -1.250  -0.1431   0.01411   0.00621  -0.0003   0.8763   0.7750
  -1.000  -0.1138   0.01407   0.00614  -0.0004   0.8660   0.7850
  -0.750  -0.0846   0.01402   0.00604  -0.0005   0.8567   0.7959
  -0.500  -0.0565   0.01401   0.00604  -0.0003   0.8455   0.8052
  -0.250  -0.0283   0.01400   0.00602  -0.0001   0.8354   0.8152
   0.000   0.0000   0.01398   0.00596   0.0000   0.8261   0.8261
   0.250   0.0283   0.01400   0.00602   0.0001   0.8152   0.8354
   0.500   0.0565   0.01402   0.00604   0.0003   0.8052   0.8455
   0.750   0.0846   0.01402   0.00604   0.0005   0.7959   0.8567
   1.000   0.1139   0.01407   0.00614   0.0004   0.7850   0.8660
   1.250   0.1431   0.01411   0.00621   0.0003   0.7750   0.8763
   1.500   0.1718   0.01414   0.00626   0.0004   0.7654   0.8874
   1.750   0.2026   0.01422   0.00640  -0.0001   0.7544   0.8970
   2.000   0.2336   0.01428   0.00652  -0.0006   0.7441   0.9070
   2.250   0.2642   0.01433   0.00661  -0.0010   0.7344   0.9179
   2.500   0.2976   0.01441   0.00678  -0.0021   0.7225   0.9271
   2.750   0.3307   0.01447   0.00693  -0.0030   0.7098   0.9367
   3.000   0.3625   0.01451   0.00702  -0.0037   0.6947   0.9474
   3.250   0.3981   0.01449   0.00706  -0.0050   0.6755   0.9554
   3.500   0.4320   0.01447   0.00709  -0.0060   0.6494   0.9646
   3.750   0.4658   0.01443   0.00704  -0.0070   0.6165   0.9740
   4.000   0.5013   0.01444   0.00702  -0.0084   0.5747   0.9824
   4.250   0.5361   0.01454   0.00704  -0.0098   0.5208   0.9911
   4.500   0.5696   0.01488   0.00710  -0.0112   0.4327   1.0000
   4.750   0.5819   0.01562   0.00728  -0.0088   0.3196   1.0000
   5.000   0.5917   0.01683   0.00782  -0.0065   0.2033   1.0000
   5.250   0.6034   0.01794   0.00850  -0.0043   0.1317   1.0000
   5.500   0.6168   0.01890   0.00920  -0.0023   0.0967   1.0000
   5.750   0.6319   0.01972   0.00993  -0.0004   0.0781   1.0000
   6.000   0.6470   0.02055   0.01071   0.0015   0.0666   1.0000
   6.250   0.6625   0.02139   0.01157   0.0034   0.0589   1.0000
   6.500   0.6786   0.02227   0.01249   0.0052   0.0533   1.0000
   6.750   0.6953   0.02313   0.01335   0.0068   0.0484   1.0000
   7.000   0.7112   0.02424   0.01446   0.0085   0.0453   1.0000
   7.250   0.7295   0.02531   0.01564   0.0099   0.0429   1.0000
   7.500   0.7486   0.02648   0.01691   0.0112   0.0407   1.0000
   7.750   0.7681   0.02767   0.01813   0.0122   0.0387   1.0000
   8.000   0.7870   0.02912   0.01954   0.0131   0.0366   1.0000
   8.250   0.8076   0.03054   0.02115   0.0141   0.0349   1.0000
   8.500   0.8282   0.03219   0.02302   0.0150   0.0336   1.0000
   8.750   0.8477   0.03406   0.02515   0.0160   0.0327   1.0000
   9.000   0.8656   0.03609   0.02743   0.0171   0.0318   1.0000
   9.250   0.8814   0.03827   0.02989   0.0183   0.0311   1.0000
   9.500   0.8946   0.04062   0.03253   0.0196   0.0306   1.0000
   9.750   0.9055   0.04296   0.03514   0.0211   0.0300   1.0000
  10.000   0.9147   0.04513   0.03751   0.0224   0.0292   1.0000
  10.250   0.9219   0.04751   0.04004   0.0237   0.0284   1.0000
  10.500   0.9217   0.05060   0.04338   0.0254   0.0279   1.0000
  10.750   0.9136   0.05361   0.04679   0.0278   0.0275   1.0000
  11.000   0.9006   0.05679   0.05027   0.0300   0.0273   1.0000
  11.250   0.8853   0.06042   0.05416   0.0311   0.0273   1.0000
  11.500   0.8678   0.06458   0.05856   0.0310   0.0273   1.0000
  11.750   0.8484   0.06942   0.06362   0.0296   0.0273   1.0000
  12.000   0.8275   0.07509   0.06947   0.0269   0.0274   1.0000
  12.250   0.8054   0.08174   0.07628   0.0229   0.0275   1.0000
  12.500   0.7827   0.08953   0.08419   0.0176   0.0277   1.0000
  12.750   0.7607   0.09840   0.09313   0.0117   0.0279   1.0000
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