Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-615 (naca632615-il)
Reynolds number: 200,000
Max Cl/Cd: 81.65 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca632615-il-200000.txt
Download as CSV file: xf-naca632615-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-615                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3764   0.09325   0.08982  -0.0568   1.0000   0.0798
 -10.250  -0.5935   0.05839   0.05455  -0.0806   0.9889   0.0460
 -10.000  -0.5923   0.05178   0.04758  -0.0880   0.9780   0.0456
  -9.750  -0.5822   0.04586   0.04122  -0.0937   0.9707   0.0453
  -9.500  -0.5723   0.04109   0.03599  -0.0963   0.9610   0.0452
  -9.250  -0.5479   0.03637   0.03073  -0.1002   0.9568   0.0452
  -9.000  -0.5284   0.03322   0.02711  -0.1013   0.9483   0.0458
  -8.750  -0.4970   0.03023   0.02360  -0.1041   0.9443   0.0475
  -8.500  -0.4601   0.02825   0.02161  -0.1071   0.9419   0.0498
  -8.250  -0.4335   0.02676   0.01995  -0.1076   0.9345   0.0515
  -8.000  -0.4002   0.02517   0.01809  -0.1092   0.9296   0.0537
  -7.750  -0.3649   0.02341   0.01611  -0.1112   0.9261   0.0566
  -7.500  -0.3388   0.02239   0.01510  -0.1113   0.9185   0.0593
  -7.250  -0.3076   0.02138   0.01400  -0.1121   0.9127   0.0622
  -7.000  -0.2736   0.02036   0.01281  -0.1133   0.9086   0.0659
  -6.750  -0.2527   0.01945   0.01198  -0.1124   0.8991   0.0692
  -6.500  -0.2225   0.01872   0.01120  -0.1129   0.8936   0.0736
  -6.250  -0.1991   0.01802   0.01046  -0.1123   0.8855   0.0779
  -6.000  -0.1730   0.01728   0.00975  -0.1123   0.8785   0.0835
  -5.750  -0.1468   0.01668   0.00911  -0.1122   0.8719   0.0903
  -5.500  -0.1225   0.01606   0.00852  -0.1120   0.8639   0.0999
  -5.250  -0.0940   0.01531   0.00779  -0.1125   0.8585   0.1177
  -5.000  -0.0711   0.01424   0.00713  -0.1128   0.8498   0.1796
  -4.750  -0.0440   0.01277   0.00661  -0.1142   0.8437   0.3924
  -4.500  -0.0165   0.01266   0.00666  -0.1142   0.8368   0.4662
  -4.250   0.0115   0.01269   0.00667  -0.1141   0.8298   0.5034
  -4.000   0.0413   0.01274   0.00666  -0.1141   0.8248   0.5300
  -3.750   0.0674   0.01287   0.00677  -0.1136   0.8168   0.5508
  -3.500   0.0960   0.01297   0.00679  -0.1134   0.8107   0.5703
  -3.250   0.1238   0.01314   0.00692  -0.1131   0.8046   0.5895
  -3.000   0.1503   0.01334   0.00710  -0.1125   0.7975   0.6076
  -2.750   0.1781   0.01347   0.00721  -0.1119   0.7923   0.6217
  -2.500   0.2038   0.01362   0.00736  -0.1112   0.7851   0.6328
  -2.250   0.2314   0.01371   0.00740  -0.1109   0.7788   0.6454
  -2.000   0.2601   0.01380   0.00742  -0.1107   0.7741   0.6557
  -1.750   0.2860   0.01384   0.00747  -0.1103   0.7663   0.6636
  -1.500   0.3143   0.01386   0.00743  -0.1102   0.7606   0.6714
  -1.250   0.3429   0.01388   0.00739  -0.1103   0.7550   0.6794
  -1.000   0.3691   0.01394   0.00746  -0.1099   0.7482   0.6862
  -0.750   0.3995   0.01391   0.00733  -0.1104   0.7429   0.6948
  -0.500   0.4255   0.01398   0.00743  -0.1099   0.7366   0.7006
  -0.250   0.4537   0.01401   0.00743  -0.1101   0.7303   0.7087
   0.000   0.4827   0.01401   0.00738  -0.1101   0.7256   0.7151
   0.250   0.5089   0.01410   0.00750  -0.1099   0.7189   0.7220
   0.500   0.5376   0.01411   0.00749  -0.1101   0.7129   0.7298
   0.750   0.5661   0.01415   0.00749  -0.1100   0.7084   0.7361
   1.000   0.5934   0.01425   0.00762  -0.1102   0.7014   0.7447
   1.250   0.6197   0.01428   0.00768  -0.1097   0.6957   0.7507
   1.500   0.6496   0.01434   0.00768  -0.1100   0.6913   0.7588
   1.750   0.6743   0.01445   0.00789  -0.1095   0.6841   0.7656
   2.000   0.7020   0.01450   0.00793  -0.1094   0.6786   0.7733
   2.250   0.7304   0.01458   0.00800  -0.1095   0.6737   0.7812
   2.500   0.7549   0.01469   0.00822  -0.1089   0.6667   0.7889
   2.750   0.7837   0.01473   0.00824  -0.1090   0.6614   0.7971
   3.000   0.8092   0.01485   0.00841  -0.1085   0.6556   0.8050
   3.250   0.8350   0.01495   0.00858  -0.1082   0.6490   0.8138
   3.500   0.8626   0.01499   0.00862  -0.1080   0.6439   0.8221
   3.750   0.8870   0.01513   0.00885  -0.1074   0.6373   0.8309
   4.000   0.9126   0.01520   0.00898  -0.1069   0.6309   0.8404
   4.250   0.9395   0.01523   0.00901  -0.1065   0.6257   0.8491
   4.500   0.9625   0.01534   0.00924  -0.1057   0.6173   0.8598
   4.750   0.9874   0.01528   0.00918  -0.1048   0.6108   0.8693
   5.000   1.0077   0.01534   0.00936  -0.1033   0.6020   0.8802
   5.250   1.0336   0.01528   0.00929  -0.1027   0.5947   0.8918
   5.500   1.0523   0.01530   0.00944  -0.1008   0.5855   0.9050
   5.750   1.0752   0.01517   0.00928  -0.0995   0.5775   0.9189
   6.000   1.0904   0.01508   0.00934  -0.0969   0.5671   0.9365
   6.250   1.1103   0.01491   0.00922  -0.0952   0.5575   0.9597
   6.500   1.1419   0.01475   0.00909  -0.0961   0.5427   1.0000
   6.750   1.1706   0.01477   0.00913  -0.0967   0.5251   1.0000
   7.000   1.1987   0.01490   0.00928  -0.0972   0.5087   1.0000
   7.250   1.2258   0.01509   0.00951  -0.0975   0.4927   1.0000
   7.500   1.2509   0.01532   0.00977  -0.0974   0.4745   1.0000
   7.750   1.2736   0.01560   0.01005  -0.0968   0.4535   1.0000
   8.000   1.2934   0.01597   0.01041  -0.0958   0.4283   1.0000
   8.250   1.3093   0.01648   0.01084  -0.0941   0.3965   1.0000
   8.500   1.3189   0.01723   0.01142  -0.0915   0.3566   1.0000
   8.750   1.3194   0.01827   0.01221  -0.0875   0.3121   1.0000
   9.000   1.3148   0.01969   0.01336  -0.0832   0.2663   1.0000
   9.250   1.3077   0.02146   0.01484  -0.0791   0.2216   1.0000
   9.500   1.2996   0.02352   0.01665  -0.0754   0.1803   1.0000
   9.750   1.2911   0.02586   0.01874  -0.0721   0.1437   1.0000
  10.000   1.2835   0.02837   0.02103  -0.0694   0.1153   1.0000
  10.250   1.2795   0.03082   0.02336  -0.0672   0.0963   1.0000
  10.500   1.2777   0.03321   0.02569  -0.0654   0.0847   1.0000
  10.750   1.2748   0.03580   0.02821  -0.0637   0.0771   1.0000
  11.000   1.2804   0.03776   0.03024  -0.0627   0.0705   1.0000
  11.250   1.2783   0.04045   0.03288  -0.0614   0.0661   1.0000
  11.500   1.2855   0.04237   0.03492  -0.0605   0.0618   1.0000
  11.750   1.2889   0.04468   0.03723  -0.0597   0.0584   1.0000
  12.000   1.2916   0.04712   0.03968  -0.0588   0.0554   1.0000
  12.250   1.2990   0.04917   0.04182  -0.0581   0.0524   1.0000
  12.500   1.3048   0.05140   0.04407  -0.0576   0.0497   1.0000
  12.750   1.3113   0.05364   0.04628  -0.0568   0.0472   1.0000
  13.000   1.3201   0.05567   0.04845  -0.0563   0.0449   1.0000
  13.250   1.3293   0.05771   0.05053  -0.0558   0.0429   1.0000
  13.500   1.3411   0.05951   0.05226  -0.0551   0.0410   1.0000
  13.750   1.3547   0.06132   0.05417  -0.0543   0.0394   1.0000
  14.000   1.3646   0.06344   0.05643  -0.0539   0.0379   1.0000
  14.250   1.3740   0.06560   0.05869  -0.0536   0.0365   1.0000
  14.500   1.3855   0.06756   0.06065  -0.0534   0.0351   1.0000
  14.750   1.4068   0.06913   0.06222  -0.0525   0.0337   1.0000
  15.000   1.4108   0.07204   0.06537  -0.0524   0.0331   1.0000
  15.250   1.4149   0.07508   0.06864  -0.0523   0.0325   1.0000
  15.500   1.4181   0.07831   0.07209  -0.0523   0.0319   1.0000
  15.750   1.4198   0.08177   0.07577  -0.0525   0.0314   1.0000
  16.000   1.4197   0.08547   0.07967  -0.0529   0.0310   1.0000
  16.250   1.4178   0.08944   0.08385  -0.0535   0.0306   1.0000
  16.500   1.4147   0.09358   0.08817  -0.0544   0.0303   1.0000
  16.750   1.4111   0.09783   0.09260  -0.0555   0.0300   1.0000
  17.000   1.4058   0.10232   0.09726  -0.0569   0.0296   1.0000
  17.250   1.3980   0.10728   0.10239  -0.0587   0.0294   1.0000
  17.500   1.3905   0.11230   0.10757  -0.0607   0.0291   1.0000
  17.750   1.3784   0.11818   0.11365  -0.0633   0.0290   1.0000
  18.000   1.3619   0.12496   0.12067  -0.0669   0.0290   1.0000
  18.250   1.3411   0.13280   0.12875  -0.0715   0.0290   1.0000
  18.500   1.1334   0.19271   0.18979  -0.1128   0.0350   1.0000
  18.750   1.1432   0.19445   0.19154  -0.1138   0.0346   1.0000
<< Back to NACA 63(2)-615 (naca632615-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(2)-615 (naca632615-il)