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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 100,000
Max Cl/Cd: 44.59 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64210-il-100000-n5.txt
Download as CSV file: xf-naca64210-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5647   0.09085   0.08579  -0.0230   1.0000   0.0284
  -9.750  -0.5706   0.08447   0.07945  -0.0273   1.0000   0.0284
  -9.500  -0.5803   0.07716   0.07218  -0.0331   1.0000   0.0279
  -9.250  -0.5951   0.07077   0.06577  -0.0380   1.0000   0.0275
  -9.000  -0.6126   0.06581   0.06076  -0.0406   1.0000   0.0272
  -8.750  -0.6262   0.06142   0.05624  -0.0415   1.0000   0.0270
  -8.500  -0.6339   0.05710   0.05172  -0.0420   1.0000   0.0273
  -8.250  -0.6366   0.05299   0.04736  -0.0419   1.0000   0.0278
  -8.000  -0.6353   0.04906   0.04311  -0.0414   1.0000   0.0286
  -7.750  -0.6306   0.04524   0.03891  -0.0405   1.0000   0.0290
  -7.500  -0.6229   0.04158   0.03485  -0.0394   1.0000   0.0292
  -7.250  -0.6123   0.03829   0.03114  -0.0381   1.0000   0.0295
  -7.000  -0.5994   0.03535   0.02776  -0.0367   1.0000   0.0299
  -6.750  -0.5844   0.03287   0.02484  -0.0352   1.0000   0.0304
  -6.500  -0.5689   0.03059   0.02219  -0.0338   1.0000   0.0319
  -6.250  -0.5528   0.02867   0.02012  -0.0326   1.0000   0.0337
  -6.000  -0.5351   0.02701   0.01825  -0.0312   1.0000   0.0347
  -5.750  -0.5170   0.02545   0.01649  -0.0297   1.0000   0.0358
  -5.500  -0.4988   0.02407   0.01495  -0.0282   1.0000   0.0369
  -5.250  -0.4806   0.02285   0.01359  -0.0266   1.0000   0.0383
  -5.000  -0.4509   0.02178   0.01233  -0.0273   0.9956   0.0416
  -4.750  -0.4177   0.02037   0.01087  -0.0288   0.9888   0.0449
  -4.500  -0.3842   0.01927   0.00977  -0.0305   0.9818   0.0484
  -4.250  -0.3489   0.01843   0.00881  -0.0324   0.9752   0.0540
  -4.000  -0.3160   0.01757   0.00792  -0.0340   0.9672   0.0625
  -3.750  -0.2810   0.01678   0.00709  -0.0358   0.9605   0.0751
  -3.500  -0.2480   0.01582   0.00635  -0.0375   0.9527   0.1167
  -3.250  -0.2232   0.01370   0.00577  -0.0386   0.9441   0.4272
  -3.000  -0.1935   0.01332   0.00586  -0.0387   0.9365   0.5844
  -2.750  -0.1675   0.01335   0.00610  -0.0375   0.9268   0.6642
  -2.500  -0.1433   0.01365   0.00656  -0.0353   0.9184   0.7316
  -2.250  -0.1160   0.01373   0.00658  -0.0344   0.9093   0.7540
  -2.000  -0.0868   0.01368   0.00640  -0.0346   0.9001   0.7658
  -1.750  -0.0555   0.01362   0.00621  -0.0351   0.8924   0.7765
  -1.500  -0.0282   0.01358   0.00610  -0.0348   0.8824   0.7852
  -1.250   0.0008   0.01353   0.00594  -0.0349   0.8738   0.7950
  -1.000   0.0291   0.01348   0.00583  -0.0349   0.8651   0.8048
  -0.750   0.0561   0.01346   0.00576  -0.0345   0.8557   0.8139
  -0.500   0.0846   0.01341   0.00566  -0.0345   0.8481   0.8241
  -0.250   0.1105   0.01341   0.00563  -0.0340   0.8382   0.8348
   0.000   0.1373   0.01339   0.00560  -0.0336   0.8298   0.8446
   0.250   0.1640   0.01338   0.00557  -0.0332   0.8214   0.8553
   0.500   0.1901   0.01339   0.00559  -0.0327   0.8125   0.8669
   0.750   0.2173   0.01337   0.00557  -0.0323   0.8052   0.8786
   1.000   0.2434   0.01339   0.00563  -0.0319   0.7958   0.8905
   1.250   0.2715   0.01338   0.00566  -0.0317   0.7887   0.9026
   1.500   0.2995   0.01341   0.00574  -0.0317   0.7798   0.9158
   1.750   0.3299   0.01342   0.00580  -0.0322   0.7721   0.9290
   2.000   0.3621   0.01345   0.00592  -0.0331   0.7640   0.9423
   2.250   0.3968   0.01349   0.00604  -0.0346   0.7561   0.9555
   2.500   0.4337   0.01350   0.00615  -0.0364   0.7477   0.9684
   2.750   0.4710   0.01354   0.00633  -0.0385   0.7370   0.9830
   3.000   0.5060   0.01359   0.00649  -0.0402   0.7266   1.0000
   3.250   0.5274   0.01365   0.00660  -0.0389   0.7127   1.0000
   3.500   0.5481   0.01352   0.00644  -0.0370   0.6835   1.0000
   3.750   0.5673   0.01333   0.00608  -0.0344   0.6288   1.0000
   4.000   0.5876   0.01341   0.00598  -0.0325   0.5661   1.0000
   4.250   0.6096   0.01367   0.00610  -0.0312   0.5036   1.0000
   4.500   0.6227   0.01480   0.00627  -0.0287   0.3163   1.0000
   4.750   0.6328   0.01691   0.00725  -0.0270   0.1287   1.0000
   5.000   0.6516   0.01814   0.00820  -0.0259   0.0816   1.0000
   5.250   0.6723   0.01910   0.00910  -0.0251   0.0645   1.0000
   5.500   0.6930   0.02006   0.01008  -0.0242   0.0564   1.0000
   5.750   0.7138   0.02100   0.01105  -0.0233   0.0498   1.0000
   6.000   0.7340   0.02206   0.01217  -0.0224   0.0451   1.0000
   6.250   0.7549   0.02319   0.01341  -0.0214   0.0421   1.0000
   6.500   0.7763   0.02444   0.01470  -0.0206   0.0397   1.0000
   6.750   0.7982   0.02592   0.01616  -0.0200   0.0373   1.0000
   7.000   0.8217   0.02754   0.01788  -0.0195   0.0350   1.0000
   7.250   0.8463   0.02906   0.01961  -0.0190   0.0331   1.0000
   7.500   0.8707   0.03099   0.02179  -0.0185   0.0318   1.0000
   7.750   0.8941   0.03312   0.02418  -0.0180   0.0309   1.0000
   8.000   0.9155   0.03547   0.02686  -0.0172   0.0301   1.0000
   8.250   0.9345   0.03803   0.02976  -0.0163   0.0294   1.0000
   8.500   0.9511   0.04038   0.03240  -0.0154   0.0284   1.0000
   8.750   0.9655   0.04269   0.03490  -0.0146   0.0271   1.0000
   9.000   0.9737   0.04666   0.03911  -0.0135   0.0260   1.0000
   9.250   0.9798   0.04969   0.04265  -0.0118   0.0257   1.0000
   9.500   0.9815   0.05320   0.04658  -0.0100   0.0255   1.0000
   9.750   0.9785   0.05689   0.05065  -0.0082   0.0254   1.0000
  10.000   0.9705   0.06061   0.05469  -0.0064   0.0253   1.0000
  10.250   0.9566   0.06412   0.05845  -0.0043   0.0253   1.0000
  10.500   0.9405   0.06789   0.06242  -0.0032   0.0253   1.0000
  10.750   0.9227   0.07215   0.06687  -0.0034   0.0254   1.0000
  11.000   0.9040   0.07706   0.07194  -0.0048   0.0255   1.0000
  11.250   0.8852   0.08269   0.07770  -0.0075   0.0256   1.0000
  11.500   0.8665   0.08919   0.08431  -0.0114   0.0257   1.0000
  11.750   0.8498   0.09635   0.09154  -0.0159   0.0259   1.0000
  12.000   0.8343   0.10449   0.09976  -0.0216   0.0262   1.0000
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