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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 200,000
Max Cl/Cd: 60.78 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64209-il-200000.txt
Download as CSV file: xf-naca64209-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5501   0.08781   0.08429  -0.0226   1.0000   0.0388
  -9.000  -0.5573   0.08120   0.07774  -0.0295   1.0000   0.0393
  -8.750  -0.5644   0.07596   0.07250  -0.0333   1.0000   0.0390
  -8.500  -0.5823   0.07130   0.06775  -0.0374   1.0000   0.0395
  -8.250  -0.5517   0.05727   0.05367  -0.0402   1.0000   0.0404
  -8.000  -0.5498   0.04997   0.04650  -0.0405   1.0000   0.0418
  -7.750  -0.5460   0.04624   0.04275  -0.0405   1.0000   0.0428
  -7.500  -0.5894   0.05313   0.04909  -0.0409   1.0000   0.0424
  -7.250  -0.5794   0.05021   0.04612  -0.0406   1.0000   0.0439
  -7.000  -0.5698   0.04713   0.04288  -0.0403   1.0000   0.0462
  -6.500  -0.5516   0.04046   0.03564  -0.0387   1.0000   0.0547
  -6.250  -0.5399   0.04014   0.03475  -0.0369   1.0000   0.0647
  -6.000  -0.5267   0.03611   0.03099  -0.0364   1.0000   0.0680
  -5.750  -0.5155   0.03449   0.02909  -0.0348   1.0000   0.0797
  -5.500  -0.5040   0.03327   0.02762  -0.0331   1.0000   0.0928
  -5.000  -0.4600   0.02322   0.01634  -0.0280   1.0000   0.0458
  -4.750  -0.4387   0.02060   0.01318  -0.0260   1.0000   0.0425
  -4.500  -0.4187   0.01890   0.01133  -0.0246   1.0000   0.0444
  -4.250  -0.3985   0.01762   0.00991  -0.0233   1.0000   0.0491
  -4.000  -0.3625   0.01619   0.00842  -0.0253   0.9963   0.0567
  -3.750  -0.3232   0.01570   0.00781  -0.0280   0.9911   0.0624
  -3.500  -0.2845   0.01495   0.00703  -0.0305   0.9859   0.0653
  -3.250  -0.2456   0.01425   0.00638  -0.0333   0.9810   0.0695
  -3.000  -0.2081   0.01369   0.00577  -0.0356   0.9745   0.0696
  -2.750  -0.1665   0.01320   0.00525  -0.0387   0.9701   0.0692
  -2.500  -0.1295   0.01282   0.00482  -0.0408   0.9631   0.0695
  -2.250  -0.0880   0.01249   0.00443  -0.0437   0.9581   0.0704
  -2.000  -0.0483   0.01222   0.00410  -0.0463   0.9527   0.0724
  -1.750  -0.0119   0.01200   0.00385  -0.0480   0.9451   0.0767
  -1.500   0.0187   0.01015   0.00351  -0.0500   0.9381   0.4587
  -1.250   0.0478   0.00963   0.00360  -0.0502   0.9295   0.6202
  -1.000   0.0762   0.00950   0.00367  -0.0499   0.9201   0.6851
  -0.750   0.1062   0.00943   0.00368  -0.0498   0.9125   0.7235
  -0.500   0.1313   0.00943   0.00375  -0.0488   0.9016   0.7550
  -0.250   0.1569   0.00944   0.00381  -0.0479   0.8916   0.7794
   0.000   0.1817   0.00945   0.00388  -0.0466   0.8827   0.8069
   0.250   0.2038   0.00949   0.00399  -0.0448   0.8721   0.8353
   0.500   0.2247   0.00955   0.00411  -0.0427   0.8618   0.8624
   0.750   0.2461   0.00958   0.00419  -0.0407   0.8527   0.8863
   1.000   0.2640   0.00960   0.00426  -0.0376   0.8429   0.9158
   1.250   0.2870   0.00959   0.00431  -0.0360   0.8330   0.9409
   1.500   0.3250   0.00955   0.00429  -0.0374   0.8257   0.9660
   1.750   0.3744   0.00953   0.00434  -0.0416   0.8162   0.9837
   2.000   0.4178   0.00949   0.00434  -0.0450   0.8053   0.9923
   2.250   0.4526   0.00946   0.00433  -0.0466   0.7933   1.0000
   2.500   0.4682   0.00937   0.00422  -0.0440   0.7730   1.0000
   2.750   0.4837   0.00920   0.00392  -0.0409   0.7418   1.0000
   3.000   0.5032   0.00913   0.00377  -0.0389   0.7075   1.0000
   3.250   0.5268   0.00918   0.00378  -0.0379   0.6804   1.0000
   3.500   0.5512   0.00927   0.00384  -0.0370   0.6482   1.0000
   3.750   0.5738   0.00944   0.00387  -0.0357   0.5882   1.0000
   4.000   0.5859   0.01068   0.00399  -0.0328   0.3449   1.0000
   4.250   0.5936   0.01355   0.00531  -0.0307   0.0776   1.0000
   4.500   0.6162   0.01450   0.00625  -0.0299   0.0620   1.0000
   4.750   0.6373   0.01567   0.00737  -0.0290   0.0535   1.0000
   5.000   0.6613   0.01646   0.00823  -0.0284   0.0477   1.0000
   5.250   0.6837   0.01767   0.00941  -0.0276   0.0442   1.0000
   5.500   0.7064   0.01986   0.01157  -0.0267   0.0419   1.0000
   5.750   0.7328   0.02113   0.01298  -0.0262   0.0408   1.0000
   6.000   0.7590   0.02230   0.01431  -0.0258   0.0383   1.0000
   6.250   0.7851   0.02409   0.01631  -0.0252   0.0371   1.0000
   6.500   0.8108   0.02647   0.01899  -0.0245   0.0371   1.0000
   6.750   0.8348   0.02963   0.02254  -0.0235   0.0384   1.0000
   7.000   0.8546   0.03451   0.02778  -0.0224   0.0412   1.0000
   8.750   0.9315   0.06992   0.06548  -0.0145   0.0544   1.0000
   9.000   0.9244   0.07187   0.06784  -0.0126   0.0540   1.0000
   9.250   0.8988   0.07296   0.06943  -0.0103   0.0523   1.0000
   9.500   0.8774   0.07655   0.07317  -0.0093   0.0516   1.0000
   9.750   0.8561   0.08111   0.07782  -0.0105   0.0516   1.0000
  10.000   0.8348   0.08698   0.08374  -0.0141   0.0517   1.0000
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