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

NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 500,000
Max Cl/Cd: 53.66 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001064-il-500000-n5.txt
Download as CSV file: xf-naca001064-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.1037   0.08161   0.07874  -0.0186   1.0000   0.0080
 -15.750  -1.1511   0.06627   0.06307  -0.0291   1.0000   0.0078
 -15.500  -1.1767   0.05756   0.05414  -0.0350   1.0000   0.0077
 -15.250  -1.1965   0.05116   0.04753  -0.0384   1.0000   0.0078
 -15.000  -1.2119   0.04626   0.04244  -0.0400   1.0000   0.0078
 -14.750  -1.2233   0.04239   0.03839  -0.0403   1.0000   0.0079
 -14.500  -1.2305   0.03933   0.03517  -0.0398   1.0000   0.0081
 -14.250  -1.2340   0.03685   0.03255  -0.0386   1.0000   0.0082
 -14.000  -1.2344   0.03480   0.03035  -0.0371   1.0000   0.0084
 -13.750  -1.2322   0.03306   0.02848  -0.0353   1.0000   0.0086
 -13.500  -1.2281   0.03153   0.02680  -0.0333   1.0000   0.0088
 -13.250  -1.2224   0.03016   0.02530  -0.0312   1.0000   0.0091
 -13.000  -1.2155   0.02891   0.02391  -0.0290   1.0000   0.0094
 -12.750  -1.2077   0.02775   0.02261  -0.0267   1.0000   0.0097
 -12.500  -1.1982   0.02668   0.02139  -0.0244   1.0000   0.0100
 -12.250  -1.1857   0.02567   0.02021  -0.0225   1.0000   0.0103
 -12.000  -1.1727   0.02461   0.01904  -0.0208   1.0000   0.0108
 -11.750  -1.1573   0.02376   0.01812  -0.0193   1.0000   0.0114
 -11.500  -1.1400   0.02306   0.01735  -0.0180   1.0000   0.0121
 -11.250  -1.1223   0.02238   0.01658  -0.0166   1.0000   0.0127
 -11.000  -1.1048   0.02166   0.01576  -0.0152   1.0000   0.0134
 -10.750  -1.0871   0.02096   0.01494  -0.0138   1.0000   0.0140
 -10.500  -1.0694   0.02031   0.01422  -0.0124   1.0000   0.0148
 -10.250  -1.0498   0.01989   0.01378  -0.0111   1.0000   0.0157
 -10.000  -1.0300   0.01953   0.01337  -0.0099   1.0000   0.0167
  -9.750  -1.0108   0.01912   0.01290  -0.0085   1.0000   0.0178
  -9.500  -0.9918   0.01870   0.01239  -0.0071   1.0000   0.0187
  -9.000  -0.9553   0.01780   0.01140  -0.0039   1.0000   0.0205
  -8.750  -0.9360   0.01750   0.01107  -0.0025   1.0000   0.0215
  -8.500  -0.9169   0.01719   0.01072  -0.0009   1.0000   0.0227
  -8.250  -0.8979   0.01687   0.01033   0.0006   1.0000   0.0238
  -8.000  -0.8789   0.01656   0.00996   0.0022   1.0000   0.0246
  -7.750  -0.8589   0.01630   0.00962   0.0036   0.9999   0.0252
  -7.500  -0.8313   0.01550   0.00877   0.0031   0.9982   0.0267
  -7.250  -0.8018   0.01503   0.00828   0.0023   0.9964   0.0280
  -7.000  -0.7712   0.01464   0.00786   0.0013   0.9948   0.0292
  -6.750  -0.7416   0.01426   0.00743   0.0006   0.9929   0.0305
  -6.500  -0.7123   0.01387   0.00699   0.0000   0.9906   0.0315
  -6.250  -0.6819   0.01352   0.00659  -0.0008   0.9884   0.0325
  -6.000  -0.6508   0.01318   0.00620  -0.0018   0.9866   0.0330
  -5.750  -0.6201   0.01264   0.00562  -0.0027   0.9850   0.0344
  -5.500  -0.5916   0.01224   0.00520  -0.0031   0.9820   0.0361
  -5.250  -0.5616   0.01191   0.00486  -0.0038   0.9793   0.0375
  -5.000  -0.5302   0.01160   0.00453  -0.0048   0.9771   0.0388
  -4.750  -0.4983   0.01132   0.00422  -0.0059   0.9752   0.0404
  -4.500  -0.4674   0.01107   0.00394  -0.0067   0.9727   0.0420
  -4.250  -0.4397   0.01080   0.00369  -0.0067   0.9683   0.0456
  -4.000  -0.4097   0.01053   0.00345  -0.0074   0.9649   0.0522
  -3.750  -0.3791   0.01022   0.00322  -0.0081   0.9622   0.0679
  -3.500  -0.3525   0.00994   0.00303  -0.0080   0.9571   0.0875
  -3.250  -0.3247   0.00965   0.00283  -0.0081   0.9523   0.1099
  -3.000  -0.2958   0.00932   0.00264  -0.0085   0.9485   0.1431
  -2.750  -0.2701   0.00901   0.00249  -0.0082   0.9424   0.1817
  -2.500  -0.2438   0.00867   0.00232  -0.0080   0.9366   0.2268
  -2.250  -0.2188   0.00813   0.00212  -0.0077   0.9313   0.3155
  -2.000  -0.1964   0.00760   0.00196  -0.0068   0.9236   0.4095
  -1.750  -0.1726   0.00708   0.00179  -0.0061   0.9176   0.5067
  -1.500  -0.1506   0.00666   0.00171  -0.0050   0.9093   0.5919
  -1.250  -0.1266   0.00633   0.00164  -0.0040   0.9026   0.6642
  -1.000  -0.1037   0.00607   0.00164  -0.0028   0.8940   0.7306
  -0.750  -0.0781   0.00593   0.00164  -0.0020   0.8866   0.7737
  -0.500  -0.0524   0.00585   0.00166  -0.0013   0.8776   0.8054
  -0.250  -0.0263   0.00580   0.00170  -0.0007   0.8684   0.8342
   0.000   0.0000   0.00579   0.00171   0.0000   0.8548   0.8549
   0.250   0.0263   0.00580   0.00170   0.0007   0.8341   0.8684
   0.500   0.0524   0.00585   0.00166   0.0014   0.8053   0.8776
   0.750   0.0781   0.00593   0.00164   0.0020   0.7738   0.8866
   1.000   0.1037   0.00607   0.00164   0.0028   0.7315   0.8940
   1.250   0.1267   0.00633   0.00164   0.0040   0.6648   0.9026
   1.500   0.1507   0.00665   0.00171   0.0049   0.5937   0.9093
   1.750   0.1726   0.00708   0.00179   0.0061   0.5065   0.9177
   2.000   0.1963   0.00761   0.00196   0.0069   0.4086   0.9236
   2.250   0.2188   0.00813   0.00212   0.0077   0.3148   0.9313
   2.500   0.2438   0.00868   0.00232   0.0080   0.2265   0.9366
   2.750   0.2701   0.00902   0.00249   0.0082   0.1815   0.9424
   3.000   0.2958   0.00932   0.00264   0.0085   0.1434   0.9485
   3.250   0.3247   0.00965   0.00283   0.0081   0.1099   0.9523
   3.500   0.3525   0.00994   0.00303   0.0080   0.0875   0.9571
   3.750   0.3791   0.01022   0.00322   0.0081   0.0679   0.9622
   4.000   0.4097   0.01053   0.00345   0.0073   0.0522   0.9649
   4.250   0.4397   0.01080   0.00369   0.0067   0.0455   0.9683
   4.500   0.4674   0.01107   0.00394   0.0067   0.0420   0.9727
   4.750   0.4983   0.01132   0.00422   0.0058   0.0404   0.9752
   5.000   0.5303   0.01160   0.00453   0.0048   0.0388   0.9771
   5.250   0.5617   0.01191   0.00486   0.0038   0.0375   0.9793
   5.500   0.5917   0.01224   0.00520   0.0031   0.0361   0.9820
   5.750   0.6202   0.01264   0.00563   0.0027   0.0344   0.9850
   6.000   0.6509   0.01318   0.00620   0.0018   0.0330   0.9866
   6.250   0.6820   0.01352   0.00659   0.0008   0.0325   0.9885
   6.500   0.7123   0.01387   0.00699   0.0000   0.0315   0.9906
   6.750   0.7417   0.01426   0.00743  -0.0006   0.0305   0.9930
   7.000   0.7714   0.01464   0.00786  -0.0014   0.0292   0.9948
   7.250   0.8019   0.01503   0.00828  -0.0023   0.0280   0.9964
   7.500   0.8315   0.01550   0.00877  -0.0031   0.0267   0.9982
   7.750   0.8590   0.01630   0.00963  -0.0036   0.0252   0.9999
   8.000   0.8789   0.01656   0.00996  -0.0022   0.0246   1.0000
   8.250   0.8979   0.01687   0.01033  -0.0006   0.0238   1.0000
   8.500   0.9168   0.01719   0.01072   0.0009   0.0227   1.0000
   8.750   0.9360   0.01750   0.01107   0.0025   0.0215   1.0000
   9.000   0.9552   0.01780   0.01140   0.0039   0.0205   1.0000
   9.250   0.9740   0.01817   0.01181   0.0054   0.0196   1.0000
   9.500   0.9918   0.01870   0.01239   0.0071   0.0187   1.0000
   9.750   1.0109   0.01912   0.01289   0.0085   0.0178   1.0000
  10.000   1.0300   0.01953   0.01338   0.0099   0.0167   1.0000
  10.250   1.0498   0.01989   0.01378   0.0111   0.0157   1.0000
  10.500   1.0694   0.02031   0.01421   0.0123   0.0148   1.0000
  10.750   1.0872   0.02096   0.01494   0.0138   0.0140   1.0000
  11.000   1.1049   0.02166   0.01576   0.0152   0.0134   1.0000
  11.250   1.1225   0.02238   0.01658   0.0166   0.0127   1.0000
  11.500   1.1402   0.02306   0.01735   0.0179   0.0121   1.0000
  11.750   1.1574   0.02376   0.01812   0.0192   0.0114   1.0000
  12.000   1.1730   0.02461   0.01904   0.0207   0.0108   1.0000
  12.250   1.1859   0.02567   0.02022   0.0225   0.0103   1.0000
  12.500   1.1985   0.02668   0.02140   0.0243   0.0100   1.0000
  12.750   1.2081   0.02776   0.02261   0.0266   0.0097   1.0000
  13.000   1.2160   0.02891   0.02391   0.0289   0.0094   1.0000
  13.250   1.2229   0.03017   0.02530   0.0311   0.0091   1.0000
  13.500   1.2285   0.03154   0.02681   0.0332   0.0088   1.0000
  13.750   1.2328   0.03306   0.02847   0.0352   0.0086   1.0000
  14.000   1.2350   0.03481   0.03036   0.0370   0.0084   1.0000
  14.250   1.2347   0.03686   0.03255   0.0385   0.0082   1.0000
  14.500   1.2314   0.03932   0.03517   0.0396   0.0081   1.0000
  14.750   1.2242   0.04239   0.03839   0.0402   0.0079   1.0000
  15.000   1.2131   0.04623   0.04241   0.0399   0.0078   1.0000
  15.250   1.1977   0.05114   0.04751   0.0382   0.0078   1.0000
  15.500   1.1783   0.05750   0.05407   0.0348   0.0077   1.0000
  15.750   1.1526   0.06625   0.06306   0.0289   0.0078   1.0000
  16.000   1.1041   0.08188   0.07902   0.0181   0.0080   1.0000
<< Back to NACA 0010-64 (naca001064-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0010-64 (naca001064-il)