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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 200,000
Max Cl/Cd: 54.05 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64210-il-200000-n5.txt
Download as CSV file: xf-naca64210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5901   0.08787   0.08426  -0.0228   1.0000   0.0159
 -10.250  -0.5981   0.08071   0.07716  -0.0273   1.0000   0.0158
 -10.000  -0.6122   0.07136   0.06779  -0.0346   1.0000   0.0157
  -9.750  -0.6291   0.06478   0.06116  -0.0398   1.0000   0.0155
  -9.500  -0.6482   0.05958   0.05586  -0.0427   1.0000   0.0154
  -9.250  -0.6665   0.05543   0.05158  -0.0429   1.0000   0.0153
  -9.000  -0.6792   0.05047   0.04637  -0.0429   1.0000   0.0154
  -8.750  -0.6866   0.04550   0.04106  -0.0423   1.0000   0.0155
  -8.500  -0.6885   0.04078   0.03591  -0.0412   1.0000   0.0157
  -8.250  -0.6848   0.03663   0.03126  -0.0399   1.0000   0.0159
  -8.000  -0.6773   0.03295   0.02721  -0.0387   1.0000   0.0163
  -7.750  -0.6637   0.03068   0.02471  -0.0376   1.0000   0.0167
  -7.500  -0.6476   0.02915   0.02299  -0.0366   1.0000   0.0174
  -7.250  -0.6307   0.02789   0.02156  -0.0355   1.0000   0.0183
  -7.000  -0.6138   0.02655   0.02002  -0.0342   1.0000   0.0195
  -6.750  -0.5976   0.02481   0.01798  -0.0325   1.0000   0.0203
  -6.500  -0.5689   0.02284   0.01567  -0.0333   0.9951   0.0211
  -6.250  -0.5362   0.02126   0.01380  -0.0346   0.9886   0.0219
  -6.000  -0.5042   0.01955   0.01192  -0.0361   0.9826   0.0235
  -5.750  -0.4713   0.01856   0.01088  -0.0377   0.9762   0.0252
  -5.500  -0.4397   0.01750   0.00973  -0.0388   0.9684   0.0264
  -5.250  -0.4071   0.01653   0.00867  -0.0401   0.9615   0.0280
  -5.000  -0.3758   0.01570   0.00772  -0.0411   0.9531   0.0298
  -4.750  -0.3449   0.01497   0.00692  -0.0420   0.9445   0.0318
  -4.500  -0.3143   0.01417   0.00611  -0.0430   0.9361   0.0361
  -4.250  -0.2854   0.01364   0.00548  -0.0434   0.9259   0.0399
  -4.000  -0.2566   0.01315   0.00490  -0.0438   0.9164   0.0446
  -3.750  -0.2281   0.01271   0.00443  -0.0441   0.9069   0.0543
  -3.500  -0.2015   0.01222   0.00401  -0.0440   0.8963   0.0736
  -3.250  -0.1765   0.01137   0.00355  -0.0441   0.8860   0.1704
  -3.000  -0.1545   0.01003   0.00315  -0.0440   0.8762   0.4012
  -2.750  -0.1300   0.00960   0.00310  -0.0434   0.8661   0.5226
  -2.500  -0.1042   0.00944   0.00307  -0.0428   0.8564   0.5805
  -2.250  -0.0794   0.00935   0.00314  -0.0418   0.8475   0.6470
  -2.000  -0.0547   0.00935   0.00324  -0.0407   0.8376   0.6914
  -1.750  -0.0280   0.00934   0.00319  -0.0403   0.8285   0.7070
  -1.500  -0.0007   0.00932   0.00310  -0.0400   0.8200   0.7177
  -1.250   0.0265   0.00929   0.00303  -0.0397   0.8106   0.7257
  -1.000   0.0540   0.00928   0.00295  -0.0396   0.8020   0.7346
  -0.750   0.0811   0.00927   0.00291  -0.0393   0.7930   0.7430
  -0.500   0.1085   0.00926   0.00288  -0.0391   0.7845   0.7518
  -0.250   0.1359   0.00927   0.00285  -0.0389   0.7764   0.7607
   0.000   0.1630   0.00927   0.00286  -0.0387   0.7674   0.7694
   0.250   0.1902   0.00929   0.00286  -0.0385   0.7594   0.7791
   0.500   0.2172   0.00931   0.00289  -0.0382   0.7507   0.7884
   0.750   0.2443   0.00933   0.00293  -0.0380   0.7431   0.7975
   1.000   0.2714   0.00936   0.00298  -0.0377   0.7349   0.8077
   1.250   0.2980   0.00940   0.00305  -0.0374   0.7268   0.8175
   1.500   0.3246   0.00944   0.00312  -0.0370   0.7192   0.8275
   1.750   0.3514   0.00948   0.00322  -0.0367   0.7113   0.8380
   2.000   0.3777   0.00953   0.00332  -0.0362   0.7034   0.8487
   2.250   0.4035   0.00957   0.00343  -0.0356   0.6931   0.8595
   2.500   0.4292   0.00962   0.00353  -0.0350   0.6830   0.8708
   2.750   0.4543   0.00965   0.00360  -0.0342   0.6676   0.8829
   3.000   0.4774   0.00967   0.00355  -0.0328   0.6320   0.8958
   3.250   0.4997   0.00977   0.00349  -0.0314   0.5797   0.9099
   3.500   0.5237   0.00992   0.00355  -0.0304   0.5385   0.9250
   3.750   0.5486   0.01015   0.00365  -0.0298   0.4833   0.9413
   4.000   0.5704   0.01113   0.00391  -0.0292   0.3180   0.9619
   4.250   0.5955   0.01260   0.00459  -0.0301   0.1517   1.0000
   4.500   0.6162   0.01362   0.00519  -0.0295   0.0759   1.0000
   4.750   0.6398   0.01429   0.00573  -0.0292   0.0529   1.0000
   5.000   0.6641   0.01487   0.00632  -0.0289   0.0432   1.0000
   5.250   0.6876   0.01555   0.00701  -0.0285   0.0371   1.0000
   5.500   0.7112   0.01622   0.00775  -0.0280   0.0340   1.0000
   5.750   0.7346   0.01688   0.00848  -0.0276   0.0310   1.0000
   6.000   0.7574   0.01762   0.00926  -0.0271   0.0280   1.0000
   6.250   0.7773   0.01879   0.01044  -0.0262   0.0258   1.0000
   6.500   0.8000   0.01964   0.01139  -0.0255   0.0248   1.0000
   6.750   0.8223   0.02063   0.01247  -0.0249   0.0237   1.0000
   7.000   0.8449   0.02174   0.01366  -0.0242   0.0228   1.0000
   7.250   0.8676   0.02295   0.01499  -0.0236   0.0219   1.0000
   7.500   0.8906   0.02425   0.01641  -0.0230   0.0211   1.0000
   7.750   0.9132   0.02540   0.01766  -0.0226   0.0202   1.0000
   8.000   0.9348   0.02666   0.01898  -0.0221   0.0192   1.0000
   8.250   0.9552   0.02891   0.02140  -0.0215   0.0183   1.0000
   8.500   0.9759   0.03068   0.02345  -0.0207   0.0179   1.0000
   8.750   0.9945   0.03282   0.02596  -0.0198   0.0175   1.0000
   9.000   1.0101   0.03538   0.02890  -0.0185   0.0170   1.0000
   9.250   1.0228   0.03804   0.03195  -0.0171   0.0164   1.0000
   9.500   1.0328   0.04064   0.03490  -0.0155   0.0156   1.0000
   9.750   1.0419   0.04278   0.03729  -0.0141   0.0149   1.0000
  10.000   1.0474   0.04519   0.03995  -0.0125   0.0145   1.0000
  10.250   1.0469   0.04809   0.04312  -0.0106   0.0142   1.0000
  10.500   1.0407   0.05081   0.04607  -0.0081   0.0140   1.0000
  10.750   1.0288   0.05390   0.04939  -0.0058   0.0139   1.0000
  11.000   1.0147   0.05732   0.05302  -0.0045   0.0138   1.0000
  11.250   0.9954   0.06179   0.05772  -0.0042   0.0138   1.0000
  11.500   0.9752   0.06683   0.06296  -0.0054   0.0138   1.0000
  11.750   0.9483   0.07378   0.07014  -0.0084   0.0139   1.0000
  12.000   0.8925   0.08877   0.08543  -0.0180   0.0144   1.0000
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