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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 200,000
Max Cl/Cd: 62.01 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63209-il-200000.txt
Download as CSV file: xf-naca63209-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5555   0.08559   0.08214  -0.0190   1.0000   0.0479
  -8.750  -0.5607   0.08025   0.07685  -0.0232   1.0000   0.0489
  -8.500  -0.5725   0.07376   0.07040  -0.0298   1.0000   0.0493
  -8.250  -0.5856   0.06859   0.06519  -0.0341   1.0000   0.0496
  -8.000  -0.5983   0.06376   0.06006  -0.0383   1.0000   0.0517
  -7.750  -0.6032   0.06183   0.05763  -0.0393   1.0000   0.0527
  -7.500  -0.5543   0.04238   0.03883  -0.0396   1.0000   0.0558
  -7.250  -0.5468   0.03883   0.03522  -0.0396   1.0000   0.0581
  -7.000  -0.5409   0.03495   0.03113  -0.0397   1.0000   0.0619
  -6.750  -0.5398   0.03003   0.02571  -0.0398   1.0000   0.0676
  -6.500  -0.5258   0.02711   0.02288  -0.0392   1.0000   0.0705
  -6.250  -0.5178   0.02432   0.01967  -0.0383   1.0000   0.0812
  -6.000  -0.5044   0.02220   0.01767  -0.0372   1.0000   0.0866
  -5.750  -0.5023   0.02905   0.02292  -0.0352   1.0000   0.0505
  -5.500  -0.4807   0.02634   0.01949  -0.0326   1.0000   0.0405
  -5.250  -0.4630   0.02275   0.01564  -0.0312   1.0000   0.0392
  -5.000  -0.4440   0.02144   0.01407  -0.0295   1.0000   0.0399
  -4.750  -0.4252   0.01921   0.01162  -0.0282   1.0000   0.0417
  -4.500  -0.4057   0.01765   0.00998  -0.0268   1.0000   0.0428
  -4.250  -0.3863   0.01654   0.00883  -0.0255   1.0000   0.0444
  -4.000  -0.3665   0.01566   0.00791  -0.0243   1.0000   0.0466
  -3.750  -0.3311   0.01493   0.00712  -0.0261   0.9962   0.0519
  -3.500  -0.2933   0.01367   0.00591  -0.0286   0.9911   0.0590
  -3.250  -0.2532   0.01281   0.00504  -0.0315   0.9854   0.0741
  -3.000  -0.2196   0.01006   0.00414  -0.0347   0.9809   0.4679
  -2.750  -0.1851   0.00965   0.00429  -0.0359   0.9737   0.6342
  -2.500  -0.1453   0.00964   0.00435  -0.0380   0.9685   0.6899
  -2.250  -0.1102   0.00967   0.00440  -0.0391   0.9606   0.7304
  -2.000  -0.0741   0.00982   0.00465  -0.0399   0.9555   0.7760
  -1.750  -0.0440   0.00989   0.00473  -0.0397   0.9462   0.8022
  -1.500  -0.0094   0.00987   0.00468  -0.0406   0.9394   0.8177
  -1.250   0.0208   0.00983   0.00461  -0.0407   0.9300   0.8315
  -1.000   0.0495   0.00980   0.00456  -0.0406   0.9203   0.8444
  -0.750   0.0780   0.00975   0.00449  -0.0402   0.9119   0.8563
  -0.500   0.1024   0.00972   0.00445  -0.0390   0.9009   0.8687
  -0.250   0.1261   0.00969   0.00441  -0.0377   0.8900   0.8816
   0.000   0.1498   0.00965   0.00436  -0.0364   0.8799   0.8948
   0.250   0.1735   0.00959   0.00429  -0.0350   0.8704   0.9085
   0.500   0.1967   0.00954   0.00425  -0.0337   0.8591   0.9232
   0.750   0.2225   0.00948   0.00419  -0.0329   0.8486   0.9381
   1.000   0.2533   0.00942   0.00412  -0.0332   0.8394   0.9521
   1.250   0.2895   0.00936   0.00407  -0.0347   0.8292   0.9646
   1.500   0.3297   0.00932   0.00406  -0.0373   0.8184   0.9758
   1.750   0.3715   0.00929   0.00404  -0.0402   0.8076   0.9864
   2.000   0.4142   0.00924   0.00401  -0.0433   0.7959   0.9971
   2.250   0.4370   0.00925   0.00404  -0.0426   0.7821   1.0000
   2.500   0.4556   0.00929   0.00407  -0.0409   0.7664   1.0000
   2.750   0.4769   0.00927   0.00402  -0.0394   0.7457   1.0000
   3.000   0.4995   0.00921   0.00388  -0.0379   0.7164   1.0000
   3.250   0.5234   0.00919   0.00380  -0.0368   0.6818   1.0000
   3.500   0.5489   0.00928   0.00385  -0.0362   0.6530   1.0000
   3.750   0.5742   0.00940   0.00392  -0.0354   0.6162   1.0000
   4.000   0.5978   0.00964   0.00398  -0.0344   0.5512   1.0000
   4.250   0.6142   0.01068   0.00418  -0.0324   0.3629   1.0000
   4.500   0.6225   0.01368   0.00551  -0.0305   0.0805   1.0000
   4.750   0.6454   0.01467   0.00644  -0.0299   0.0596   1.0000
   5.000   0.6679   0.01575   0.00754  -0.0291   0.0515   1.0000
   5.250   0.6905   0.01681   0.00860  -0.0283   0.0466   1.0000
   5.500   0.7115   0.01866   0.01043  -0.0273   0.0434   1.0000
   5.750   0.7370   0.01950   0.01138  -0.0268   0.0403   1.0000
   6.000   0.7623   0.02086   0.01282  -0.0263   0.0383   1.0000
   6.250   0.7881   0.02250   0.01457  -0.0257   0.0371   1.0000
   6.500   0.8141   0.02447   0.01672  -0.0252   0.0364   1.0000
   6.750   0.8396   0.02689   0.01944  -0.0244   0.0365   1.0000
   7.000   0.8630   0.02887   0.02160  -0.0240   0.0349   1.0000
   7.250   0.8852   0.03162   0.02466  -0.0231   0.0345   1.0000
   7.500   0.9004   0.03828   0.03221  -0.0206   0.0415   1.0000
  10.250   0.7939   0.08696   0.08383  -0.0103   0.0557   1.0000
  10.500   0.7738   0.09312   0.09006  -0.0131   0.0558   1.0000
  10.750   0.7510   0.09998   0.09698  -0.0172   0.0558   1.0000
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