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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 100,000
Max Cl/Cd: 39.26 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63015a-il-100000-n5.txt
Download as CSV file: xf-n63015a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-015A 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.7891   0.12005   0.11448  -0.0105   1.0000   0.0326
 -15.250  -0.8278   0.10689   0.10116  -0.0188   1.0000   0.0322
 -15.000  -0.8603   0.09665   0.09073  -0.0252   1.0000   0.0319
 -14.750  -0.8885   0.08835   0.08220  -0.0300   1.0000   0.0318
 -14.500  -0.9128   0.08139   0.07501  -0.0335   1.0000   0.0317
 -14.250  -0.9338   0.07539   0.06877  -0.0361   1.0000   0.0317
 -14.000  -0.9515   0.07015   0.06328  -0.0378   1.0000   0.0318
 -13.750  -0.9660   0.06555   0.05841  -0.0389   1.0000   0.0319
 -13.500  -0.9772   0.06146   0.05405  -0.0393   1.0000   0.0321
 -13.250  -0.9850   0.05782   0.05013  -0.0393   1.0000   0.0323
 -13.000  -0.9894   0.05457   0.04659  -0.0390   1.0000   0.0326
 -12.750  -0.9893   0.05171   0.04348  -0.0383   1.0000   0.0329
 -12.500  -0.9816   0.04940   0.04109  -0.0377   1.0000   0.0334
 -12.250  -0.9735   0.04732   0.03892  -0.0371   1.0000   0.0340
 -12.000  -0.9648   0.04536   0.03684  -0.0363   1.0000   0.0347
 -11.750  -0.9549   0.04350   0.03485  -0.0355   1.0000   0.0355
 -11.500  -0.9444   0.04175   0.03297  -0.0346   1.0000   0.0365
 -11.250  -0.9327   0.04009   0.03113  -0.0337   1.0000   0.0379
 -11.000  -0.9196   0.03851   0.02934  -0.0327   1.0000   0.0394
 -10.500  -0.8942   0.03559   0.02641  -0.0307   1.0000   0.0423
 -10.250  -0.8812   0.03425   0.02501  -0.0295   1.0000   0.0440
 -10.000  -0.8680   0.03294   0.02361  -0.0283   1.0000   0.0460
  -9.750  -0.8560   0.03167   0.02226  -0.0268   1.0000   0.0482
  -9.500  -0.8466   0.03046   0.02108  -0.0252   1.0000   0.0508
  -9.250  -0.8360   0.02939   0.01995  -0.0234   1.0000   0.0542
  -9.000  -0.8268   0.02832   0.01883  -0.0213   1.0000   0.0577
  -8.750  -0.8190   0.02732   0.01786  -0.0189   1.0000   0.0617
  -8.500  -0.8085   0.02643   0.01691  -0.0167   1.0000   0.0673
  -8.250  -0.8003   0.02544   0.01598  -0.0142   1.0000   0.0733
  -8.000  -0.7911   0.02456   0.01511  -0.0117   1.0000   0.0814
  -7.750  -0.7820   0.02375   0.01432  -0.0091   1.0000   0.0916
  -7.500  -0.7747   0.02294   0.01357  -0.0061   1.0000   0.1039
  -7.250  -0.7686   0.02215   0.01290  -0.0030   1.0000   0.1194
  -7.000  -0.7635   0.02138   0.01227   0.0003   1.0000   0.1389
  -6.750  -0.7592   0.02065   0.01169   0.0038   1.0000   0.1646
  -6.500  -0.7402   0.01958   0.01091   0.0040   0.9938   0.2142
  -6.250  -0.7137   0.01830   0.01014   0.0027   0.9830   0.2985
  -6.000  -0.6854   0.01746   0.00977   0.0016   0.9729   0.3896
  -5.750  -0.6546   0.01710   0.00958   0.0006   0.9626   0.4498
  -5.500  -0.6230   0.01692   0.00940  -0.0003   0.9525   0.4891
  -5.250  -0.5891   0.01680   0.00924  -0.0016   0.9439   0.5187
  -5.000  -0.5587   0.01674   0.00915  -0.0020   0.9330   0.5410
  -4.750  -0.5277   0.01670   0.00905  -0.0026   0.9232   0.5621
  -4.500  -0.4965   0.01667   0.00892  -0.0031   0.9138   0.5827
  -4.250  -0.4686   0.01667   0.00887  -0.0029   0.9029   0.6003
  -4.000  -0.4380   0.01666   0.00879  -0.0032   0.8941   0.6154
  -3.750  -0.4095   0.01666   0.00875  -0.0031   0.8836   0.6274
  -3.500  -0.3810   0.01662   0.00864  -0.0030   0.8741   0.6382
  -3.250  -0.3531   0.01652   0.00843  -0.0029   0.8647   0.6492
  -3.000  -0.3250   0.01649   0.00836  -0.0028   0.8547   0.6571
  -2.750  -0.2967   0.01637   0.00813  -0.0028   0.8466   0.6662
  -2.500  -0.2697   0.01633   0.00806  -0.0025   0.8362   0.6735
  -2.250  -0.2424   0.01623   0.00785  -0.0024   0.8280   0.6822
  -2.000  -0.2150   0.01620   0.00780  -0.0021   0.8184   0.6891
  -1.750  -0.1884   0.01611   0.00763  -0.0019   0.8101   0.6980
  -1.500  -0.1608   0.01609   0.00760  -0.0017   0.8011   0.7046
  -1.250  -0.1347   0.01602   0.00745  -0.0014   0.7929   0.7137
  -1.000  -0.1070   0.01601   0.00745  -0.0011   0.7842   0.7200
  -0.750  -0.0807   0.01597   0.00735  -0.0008   0.7763   0.7289
  -0.500  -0.0535   0.01597   0.00736  -0.0006   0.7678   0.7357
  -0.250  -0.0269   0.01594   0.00731  -0.0003   0.7601   0.7443
   0.000   0.0000   0.01595   0.00733   0.0000   0.7516   0.7516
   0.250   0.0269   0.01594   0.00731   0.0003   0.7443   0.7601
   0.500   0.0535   0.01597   0.00736   0.0006   0.7357   0.7678
   0.750   0.0807   0.01597   0.00735   0.0008   0.7289   0.7763
   1.000   0.1071   0.01601   0.00745   0.0011   0.7200   0.7842
   1.250   0.1347   0.01602   0.00745   0.0014   0.7137   0.7929
   1.500   0.1609   0.01609   0.00760   0.0017   0.7046   0.8011
   1.750   0.1885   0.01611   0.00763   0.0019   0.6980   0.8101
   2.000   0.2150   0.01620   0.00780   0.0021   0.6891   0.8184
   2.250   0.2424   0.01623   0.00785   0.0024   0.6822   0.8280
   2.500   0.2697   0.01633   0.00806   0.0025   0.6735   0.8362
   2.750   0.2967   0.01637   0.00813   0.0028   0.6662   0.8466
   3.000   0.3250   0.01649   0.00836   0.0028   0.6571   0.8547
   3.250   0.3531   0.01652   0.00843   0.0029   0.6492   0.8647
   3.500   0.3810   0.01662   0.00864   0.0030   0.6382   0.8741
   3.750   0.4095   0.01666   0.00875   0.0031   0.6273   0.8836
   4.000   0.4380   0.01666   0.00879   0.0032   0.6154   0.8941
   4.250   0.4686   0.01667   0.00887   0.0029   0.6002   0.9029
   4.500   0.4966   0.01667   0.00892   0.0031   0.5827   0.9138
   4.750   0.5277   0.01670   0.00905   0.0026   0.5621   0.9232
   5.000   0.5587   0.01674   0.00914   0.0020   0.5410   0.9331
   5.250   0.5891   0.01680   0.00924   0.0016   0.5187   0.9440
   5.500   0.6231   0.01692   0.00940   0.0003   0.4891   0.9525
   5.750   0.6546   0.01710   0.00958  -0.0006   0.4498   0.9626
   6.000   0.6854   0.01746   0.00976  -0.0016   0.3895   0.9729
   6.250   0.7137   0.01830   0.01014  -0.0027   0.2983   0.9831
   6.500   0.7403   0.01958   0.01091  -0.0041   0.2141   0.9939
   6.750   0.7592   0.02064   0.01168  -0.0038   0.1647   1.0000
   7.000   0.7634   0.02137   0.01227  -0.0003   0.1389   1.0000
   7.250   0.7686   0.02214   0.01290   0.0030   0.1194   1.0000
   7.500   0.7748   0.02294   0.01357   0.0061   0.1039   1.0000
   7.750   0.7821   0.02375   0.01432   0.0091   0.0915   1.0000
   8.000   0.7912   0.02456   0.01511   0.0117   0.0814   1.0000
   8.250   0.8004   0.02544   0.01598   0.0142   0.0733   1.0000
   8.500   0.8086   0.02643   0.01691   0.0166   0.0672   1.0000
   8.750   0.8192   0.02732   0.01786   0.0188   0.0617   1.0000
   9.000   0.8271   0.02832   0.01883   0.0212   0.0576   1.0000
   9.250   0.8363   0.02939   0.01995   0.0234   0.0541   1.0000
   9.500   0.8470   0.03046   0.02108   0.0251   0.0507   1.0000
   9.750   0.8564   0.03167   0.02226   0.0268   0.0482   1.0000
  10.000   0.8684   0.03294   0.02361   0.0282   0.0460   1.0000
  10.250   0.8817   0.03424   0.02500   0.0295   0.0440   1.0000
  10.500   0.8947   0.03559   0.02640   0.0306   0.0423   1.0000
  10.750   0.9070   0.03697   0.02781   0.0317   0.0408   1.0000
  11.000   0.9202   0.03851   0.02934   0.0326   0.0394   1.0000
  11.250   0.9333   0.04008   0.03113   0.0336   0.0379   1.0000
  11.500   0.9450   0.04175   0.03297   0.0345   0.0365   1.0000
  11.750   0.9556   0.04350   0.03485   0.0354   0.0354   1.0000
  12.000   0.9655   0.04536   0.03684   0.0362   0.0347   1.0000
  12.250   0.9744   0.04732   0.03892   0.0370   0.0340   1.0000
  12.500   0.9825   0.04940   0.04109   0.0376   0.0334   1.0000
  12.750   0.9902   0.05171   0.04349   0.0382   0.0329   1.0000
  13.000   0.9902   0.05459   0.04661   0.0388   0.0326   1.0000
  13.250   0.9858   0.05785   0.05016   0.0392   0.0323   1.0000
  13.500   0.9781   0.06148   0.05408   0.0392   0.0321   1.0000
  13.750   0.9669   0.06557   0.05844   0.0387   0.0319   1.0000
  14.000   0.9524   0.07020   0.06333   0.0377   0.0318   1.0000
  14.250   0.9347   0.07544   0.06883   0.0359   0.0317   1.0000
  14.500   0.9137   0.08145   0.07508   0.0333   0.0317   1.0000
  14.750   0.8892   0.08846   0.08232   0.0297   0.0318   1.0000
  15.000   0.8611   0.09679   0.09087   0.0249   0.0319   1.0000
  15.250   0.8283   0.10713   0.10141   0.0184   0.0322   1.0000
  15.500   0.7894   0.12039   0.11482   0.0101   0.0326   1.0000
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