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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 100,000
Max Cl/Cd: 58.2 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a410-il-100000.txt
Download as CSV file: xf-naca64a410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3358   0.09349   0.08891  -0.0400   1.0000   0.1063
  -9.000  -0.3580   0.09116   0.08672  -0.0415   1.0000   0.1079
  -8.750  -0.3815   0.08896   0.08463  -0.0421   1.0000   0.1084
  -8.500  -0.3514   0.08404   0.07965  -0.0376   1.0000   0.1133
  -8.250  -0.3580   0.08148   0.07715  -0.0361   1.0000   0.1168
  -8.000  -0.3758   0.07914   0.07490  -0.0352   1.0000   0.1196
  -7.750  -0.4026   0.07722   0.07310  -0.0340   1.0000   0.1209
  -7.500  -0.4760   0.08218   0.07781  -0.0353   1.0000   0.1134
  -7.250  -0.4847   0.07951   0.07520  -0.0348   1.0000   0.1167
  -7.000  -0.5026   0.07604   0.07172  -0.0380   1.0000   0.1205
  -6.750  -0.5186   0.07186   0.06741  -0.0411   1.0000   0.1235
  -6.500  -0.5070   0.06941   0.06512  -0.0362   1.0000   0.1277
  -6.250  -0.5176   0.06576   0.06111  -0.0411   1.0000   0.1373
  -6.000  -0.5067   0.06259   0.05816  -0.0370   1.0000   0.1412
  -5.750  -0.5037   0.05907   0.05446  -0.0386   1.0000   0.1532
  -5.500  -0.4961   0.05617   0.05144  -0.0388   1.0000   0.1669
  -5.250  -0.4863   0.05337   0.04859  -0.0382   1.0000   0.1814
  -5.000  -0.4751   0.05065   0.04586  -0.0373   1.0000   0.1969
  -4.750  -0.4625   0.04812   0.04333  -0.0363   1.0000   0.2138
  -4.500  -0.3997   0.03769   0.03044  -0.0445   1.0000   0.0948
  -4.250  -0.3692   0.03250   0.02480  -0.0453   1.0000   0.0804
  -4.000  -0.3402   0.02929   0.02112  -0.0456   1.0000   0.0746
  -3.750  -0.3107   0.02711   0.01819  -0.0453   1.0000   0.0711
  -3.500  -0.2856   0.02554   0.01653  -0.0454   1.0000   0.0740
  -3.250  -0.2606   0.02447   0.01530  -0.0452   1.0000   0.0774
  -3.000  -0.2289   0.02325   0.01388  -0.0458   0.9987   0.0797
  -2.750  -0.1868   0.02217   0.01279  -0.0487   0.9948   0.0863
  -2.500  -0.1474   0.02147   0.01209  -0.0512   0.9898   0.0992
  -2.250  -0.1055   0.02058   0.01130  -0.0543   0.9855   0.1252
  -2.000  -0.0691   0.01773   0.01106  -0.0561   0.9845   0.6849
  -1.750  -0.0447   0.01783   0.01131  -0.0542   0.9772   0.7950
  -1.500  -0.0178   0.01784   0.01143  -0.0528   0.9711   0.8695
  -1.250   0.0169   0.01780   0.01140  -0.0540   0.9616   1.0000
  -1.000   0.0645   0.01818   0.01147  -0.0590   0.9563   1.0000
  -0.750   0.0976   0.01844   0.01154  -0.0612   0.9473   1.0000
  -0.500   0.1431   0.01881   0.01170  -0.0655   0.9420   1.0000
  -0.250   0.1730   0.01911   0.01185  -0.0669   0.9326   1.0000
   0.000   0.2175   0.01944   0.01204  -0.0707   0.9274   1.0000
   0.250   0.2445   0.01978   0.01228  -0.0714   0.9177   1.0000
   0.500   0.2888   0.02006   0.01248  -0.0750   0.9128   1.0000
   0.750   0.3147   0.02039   0.01275  -0.0753   0.9024   1.0000
   1.000   0.3506   0.02063   0.01295  -0.0771   0.8942   1.0000
   1.250   0.3899   0.02073   0.01303  -0.0794   0.8859   1.0000
   1.500   0.4207   0.02091   0.01319  -0.0802   0.8753   1.0000
   1.750   0.4720   0.02064   0.01295  -0.0841   0.8694   1.0000
   2.000   0.4973   0.02085   0.01320  -0.0838   0.8579   1.0000
   2.250   0.5267   0.02105   0.01343  -0.0842   0.8490   1.0000
   2.500   0.5628   0.02103   0.01347  -0.0855   0.8425   1.0000
   2.750   0.5888   0.02125   0.01375  -0.0852   0.8323   1.0000
   3.000   0.6306   0.02081   0.01343  -0.0869   0.8266   1.0000
   3.250   0.6556   0.02091   0.01362  -0.0862   0.8151   1.0000
   3.500   0.6835   0.02091   0.01373  -0.0858   0.8049   1.0000
   3.750   0.7235   0.02020   0.01319  -0.0867   0.7980   1.0000
   4.000   0.7587   0.01911   0.01222  -0.0859   0.7835   1.0000
   4.250   0.7855   0.01828   0.01151  -0.0838   0.7629   1.0000
   4.500   0.8207   0.01695   0.01029  -0.0825   0.7415   1.0000
   4.750   0.8464   0.01640   0.00983  -0.0805   0.7157   1.0000
   5.000   0.8719   0.01599   0.00951  -0.0786   0.6864   1.0000
   5.250   0.8941   0.01564   0.00918  -0.0760   0.6411   1.0000
   5.500   0.9091   0.01562   0.00893  -0.0721   0.5478   1.0000
   5.750   0.9011   0.01779   0.00937  -0.0653   0.2682   1.0000
   6.000   0.8949   0.02099   0.01128  -0.0605   0.1286   1.0000
   6.250   0.9025   0.02298   0.01304  -0.0572   0.0998   1.0000
   6.500   0.9192   0.02420   0.01424  -0.0553   0.0834   1.0000
   6.750   0.9371   0.02544   0.01541  -0.0536   0.0745   1.0000
   7.000   0.9594   0.02703   0.01703  -0.0524   0.0695   1.0000
   7.250   0.9844   0.02868   0.01864  -0.0518   0.0648   1.0000
   7.500   1.0141   0.03097   0.02099  -0.0519   0.0607   1.0000
   7.750   1.0456   0.03349   0.02375  -0.0520   0.0589   1.0000
   8.000   1.0741   0.03644   0.02704  -0.0515   0.0584   1.0000
   8.250   1.0983   0.03983   0.03086  -0.0505   0.0589   1.0000
   8.500   1.1172   0.04337   0.03489  -0.0489   0.0593   1.0000
   8.750   1.1309   0.04686   0.03884  -0.0467   0.0591   1.0000
   9.000   1.1415   0.05082   0.04323  -0.0445   0.0599   1.0000
   9.250   1.1537   0.05591   0.04854  -0.0431   0.0620   1.0000
   9.500   1.1451   0.06189   0.05544  -0.0381   0.0717   1.0000
   9.750   1.0791   0.06163   0.05579  -0.0281   0.0861   1.0000
  10.000   1.0232   0.06371   0.05859  -0.0199   0.0892   1.0000
  10.250   0.9835   0.06802   0.06315  -0.0156   0.0914   1.0000
  10.500   0.9494   0.07289   0.06816  -0.0134   0.0929   1.0000
  10.750   0.9186   0.07846   0.07385  -0.0126   0.0950   1.0000
  11.000   0.8850   0.08439   0.07988  -0.0130   0.0955   1.0000
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