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NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(2)-215 (naca662215-il)
Reynolds number: 50,000
Max Cl/Cd: 20.95 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca662215-il-50000-n5.txt
Download as CSV file: xf-naca662215-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-215                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4795   0.10974   0.10227  -0.0614   1.0000   0.0618
 -12.250  -0.4899   0.10369   0.09628  -0.0640   1.0000   0.0608
 -12.000  -0.5084   0.09652   0.08916  -0.0676   1.0000   0.0596
 -11.750  -0.5391   0.08961   0.08229  -0.0706   1.0000   0.0584
 -11.500  -0.5775   0.08424   0.07692  -0.0712   1.0000   0.0575
 -11.250  -0.6167   0.08059   0.07325  -0.0691   1.0000   0.0568
 -11.000  -0.6579   0.07807   0.07067  -0.0651   1.0000   0.0562
 -10.750  -0.6994   0.07624   0.06878  -0.0598   1.0000   0.0558
 -10.500  -0.7431   0.07507   0.06750  -0.0530   1.0000   0.0553
 -10.000  -0.8072   0.07223   0.06426  -0.0406   0.9992   0.0546
  -9.750  -0.8098   0.06865   0.06038  -0.0396   0.9937   0.0546
  -9.500  -0.8105   0.06529   0.05669  -0.0383   0.9884   0.0545
  -9.250  -0.8081   0.06204   0.05306  -0.0371   0.9836   0.0546
  -8.750  -0.7935   0.05602   0.04635  -0.0347   0.9750   0.0550
  -8.500  -0.7831   0.05354   0.04365  -0.0334   0.9714   0.0559
  -8.250  -0.7696   0.05149   0.04145  -0.0324   0.9680   0.0573
  -8.000  -0.7537   0.04947   0.03915  -0.0317   0.9649   0.0590
  -7.750  -0.7344   0.04737   0.03669  -0.0313   0.9622   0.0605
  -7.500  -0.7184   0.04548   0.03445  -0.0298   0.9586   0.0614
  -7.250  -0.6961   0.04364   0.03226  -0.0292   0.9558   0.0626
  -7.000  -0.6698   0.04207   0.03032  -0.0291   0.9534   0.0644
  -6.750  -0.6393   0.04055   0.02866  -0.0298   0.9518   0.0673
  -6.500  -0.6064   0.03936   0.02741  -0.0309   0.9505   0.0707
  -6.250  -0.5670   0.03834   0.02624  -0.0325   0.9497   0.0739
  -6.000  -0.5349   0.03769   0.02535  -0.0328   0.9481   0.0782
  -5.750  -0.5132   0.03687   0.02459  -0.0319   0.9456   0.0832
  -5.500  -0.4944   0.03623   0.02385  -0.0306   0.9426   0.0883
  -5.250  -0.4767   0.03553   0.02306  -0.0293   0.9396   0.0935
  -5.000  -0.4603   0.03480   0.02233  -0.0280   0.9370   0.1024
  -4.750  -0.4467   0.03404   0.02161  -0.0263   0.9346   0.1154
  -4.500  -0.4453   0.03328   0.02098  -0.0223   0.9312   0.1324
  -4.250  -0.4441   0.03208   0.02023  -0.0187   0.9275   0.1827
  -4.000  -0.4552   0.02990   0.01946  -0.0133   0.9238   0.3832
  -3.750  -0.4331   0.03213   0.02298  -0.0065   0.9221   0.7045
  -3.500  -0.3483   0.03862   0.02919  -0.0053   0.9238   0.8271
  -3.250  -0.2944   0.03936   0.02957  -0.0091   0.9233   0.8476
  -3.000  -0.2553   0.03940   0.02932  -0.0118   0.9220   0.8564
  -2.750  -0.2270   0.03935   0.02905  -0.0127   0.9201   0.8651
  -2.500  -0.2076   0.03926   0.02880  -0.0119   0.9170   0.8732
  -2.250  -0.1911   0.03915   0.02854  -0.0108   0.9138   0.8809
  -2.000  -0.1650   0.03908   0.02832  -0.0114   0.9112   0.8873
  -1.750  -0.1481   0.03902   0.02813  -0.0104   0.9081   0.8947
  -1.500  -0.1127   0.03898   0.02794  -0.0129   0.9060   0.8992
  -1.250  -0.0897   0.03897   0.02783  -0.0130   0.9033   0.9050
  -1.000  -0.0805   0.03889   0.02768  -0.0106   0.8990   0.9111
  -0.750  -0.0545   0.03886   0.02757  -0.0114   0.8955   0.9153
  -0.500  -0.0323   0.03887   0.02751  -0.0114   0.8921   0.9201
  -0.250  -0.0091   0.03893   0.02750  -0.0116   0.8890   0.9247
   0.000   0.0123   0.03894   0.02747  -0.0116   0.8850   0.9283
   0.250   0.0308   0.03896   0.02747  -0.0110   0.8803   0.9326
   0.500   0.0494   0.03903   0.02751  -0.0103   0.8762   0.9369
   0.750   0.0805   0.03917   0.02763  -0.0120   0.8729   0.9397
   1.000   0.0963   0.03922   0.02769  -0.0110   0.8673   0.9431
   1.250   0.1170   0.03932   0.02780  -0.0108   0.8622   0.9465
   1.500   0.1432   0.03949   0.02798  -0.0115   0.8580   0.9498
   1.750   0.1611   0.03962   0.02815  -0.0109   0.8521   0.9530
   2.000   0.1840   0.03976   0.02834  -0.0111   0.8460   0.9556
   2.250   0.2163   0.03997   0.02861  -0.0129   0.8415   0.9581
   2.500   0.2294   0.04015   0.02886  -0.0114   0.8342   0.9624
   2.750   0.2567   0.04036   0.02915  -0.0123   0.8281   0.9651
   3.000   0.2918   0.04061   0.02950  -0.0146   0.8234   0.9671
   3.250   0.3054   0.04082   0.02982  -0.0133   0.8141   0.9707
   3.750   0.3574   0.04128   0.03053  -0.0146   0.7988   0.9770
   4.250   0.4140   0.04167   0.03126  -0.0166   0.7816   0.9834
   4.500   0.4452   0.04180   0.03157  -0.0178   0.7731   0.9861
   4.750   0.4753   0.04187   0.03186  -0.0189   0.7632   0.9889
   5.000   0.4984   0.04199   0.03218  -0.0188   0.7512   0.9927
   5.250   0.5295   0.04193   0.03237  -0.0198   0.7400   0.9961
   5.500   0.5719   0.04148   0.03223  -0.0220   0.7299   0.9987
   5.750   0.5915   0.04105   0.03205  -0.0203   0.7149   1.0000
   6.000   0.5951   0.04020   0.03135  -0.0155   0.6921   1.0000
   6.250   0.6124   0.03691   0.02820  -0.0097   0.6457   1.0000
   6.500   0.6020   0.03577   0.02709  -0.0024   0.6033   1.0000
   6.750   0.6027   0.03418   0.02553   0.0039   0.5453   1.0000
   7.000   0.6544   0.03123   0.02101   0.0068   0.2867   1.0000
   7.250   0.6359   0.03235   0.02159   0.0130   0.2152   1.0000
   7.500   0.6211   0.03353   0.02230   0.0185   0.1620   1.0000
   7.750   0.6127   0.03467   0.02311   0.0230   0.1310   1.0000
   8.000   0.6113   0.03588   0.02406   0.0263   0.1127   1.0000
   8.250   0.6163   0.03705   0.02516   0.0286   0.0999   1.0000
   8.500   0.6264   0.03817   0.02628   0.0304   0.0912   1.0000
   8.750   0.6386   0.03937   0.02742   0.0318   0.0855   1.0000
   9.000   0.6579   0.04031   0.02849   0.0328   0.0794   1.0000
   9.250   0.6801   0.04134   0.02949   0.0333   0.0737   1.0000
   9.500   0.7220   0.04214   0.03045   0.0327   0.0692   1.0000
   9.750   0.7622   0.04325   0.03172   0.0317   0.0642   1.0000
  10.000   0.8084   0.04498   0.03343   0.0296   0.0603   1.0000
  10.250   0.8475   0.04719   0.03605   0.0283   0.0583   1.0000
  10.500   0.8733   0.04953   0.03874   0.0282   0.0565   1.0000
  10.750   0.8898   0.05177   0.04123   0.0288   0.0544   1.0000
  11.000   0.9046   0.05407   0.04371   0.0294   0.0527   1.0000
  11.250   0.9177   0.05663   0.04646   0.0301   0.0514   1.0000
  11.500   0.9274   0.05956   0.04960   0.0310   0.0508   1.0000
  11.750   0.9294   0.06262   0.05291   0.0325   0.0505   1.0000
  12.000   0.9229   0.06563   0.05624   0.0347   0.0504   1.0000
  12.250   0.9134   0.06882   0.05971   0.0366   0.0503   1.0000
  12.500   0.9017   0.07219   0.06335   0.0382   0.0503   1.0000
  12.750   0.8871   0.07585   0.06726   0.0395   0.0503   1.0000
  13.000   0.8690   0.07989   0.07154   0.0403   0.0503   1.0000
  13.250   0.8519   0.08417   0.07603   0.0404   0.0504   1.0000
  13.500   0.8325   0.08894   0.08098   0.0398   0.0505   1.0000
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