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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.62 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64209-il-1000000.txt
Download as CSV file: xf-naca64209-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6965   0.03106   0.02823  -0.0397   1.0000   0.0084
  -8.000  -0.7009   0.02254   0.01895  -0.0372   1.0000   0.0084
  -7.750  -0.6917   0.01770   0.01350  -0.0352   1.0000   0.0086
  -7.500  -0.6755   0.01545   0.01093  -0.0337   1.0000   0.0088
  -7.250  -0.6519   0.01391   0.00916  -0.0334   0.9990   0.0091
  -7.000  -0.6194   0.01272   0.00781  -0.0349   0.9959   0.0094
  -6.750  -0.5870   0.01184   0.00680  -0.0364   0.9924   0.0101
  -6.500  -0.5547   0.01104   0.00589  -0.0377   0.9883   0.0107
  -6.250  -0.5208   0.01035   0.00507  -0.0394   0.9847   0.0111
  -6.000  -0.4881   0.00980   0.00442  -0.0407   0.9791   0.0116
  -5.750  -0.4553   0.00938   0.00394  -0.0419   0.9722   0.0121
  -5.500  -0.4237   0.00911   0.00366  -0.0428   0.9637   0.0131
  -5.250  -0.3932   0.00905   0.00365  -0.0434   0.9541   0.0146
  -5.000  -0.3640   0.00945   0.00418  -0.0435   0.9428   0.0158
  -4.750  -0.3367   0.00949   0.00412  -0.0432   0.9309   0.0212
  -4.500  -0.3092   0.00969   0.00430  -0.0430   0.9196   0.0227
  -4.250  -0.2829   0.00955   0.00416  -0.0428   0.9085   0.0252
  -4.000  -0.2562   0.00953   0.00410  -0.0426   0.8978   0.0272
  -3.750  -0.2290   0.00950   0.00402  -0.0425   0.8870   0.0287
  -3.500  -0.2012   0.00969   0.00418  -0.0425   0.8768   0.0298
  -3.250  -0.1757   0.00909   0.00349  -0.0422   0.8666   0.0315
  -3.000  -0.1495   0.00868   0.00304  -0.0421   0.8564   0.0328
  -2.750  -0.1225   0.00840   0.00274  -0.0420   0.8465   0.0340
  -2.500  -0.0954   0.00818   0.00250  -0.0420   0.8371   0.0360
  -2.250  -0.0682   0.00800   0.00227  -0.0419   0.8274   0.0374
  -2.000  -0.0406   0.00782   0.00206  -0.0419   0.8174   0.0382
  -1.750  -0.0129   0.00767   0.00186  -0.0419   0.8078   0.0376
  -1.250   0.0427   0.00743   0.00152  -0.0419   0.7886   0.0364
  -1.000   0.0707   0.00735   0.00140  -0.0419   0.7794   0.0358
  -0.500   0.1266   0.00721   0.00121  -0.0420   0.7599   0.0349
  -0.250   0.1546   0.00715   0.00114  -0.0420   0.7503   0.0346
   0.000   0.1825   0.00712   0.00107  -0.0420   0.7412   0.0343
   0.250   0.2106   0.00707   0.00102  -0.0421   0.7312   0.0342
   0.500   0.2386   0.00704   0.00098  -0.0421   0.7207   0.0342
   0.750   0.2666   0.00703   0.00095  -0.0422   0.7095   0.0345
   1.000   0.2944   0.00703   0.00092  -0.0422   0.6972   0.0353
   1.250   0.3221   0.00704   0.00090  -0.0421   0.6792   0.0376
   1.500   0.3474   0.00558   0.00081  -0.0427   0.6469   0.5823
   1.750   0.3736   0.00538   0.00091  -0.0425   0.6189   0.6985
   2.000   0.4005   0.00537   0.00100  -0.0424   0.5988   0.7452
   2.250   0.4275   0.00542   0.00109  -0.0422   0.5749   0.7756
   2.500   0.4540   0.00555   0.00120  -0.0419   0.5399   0.7983
   2.750   0.4792   0.00580   0.00133  -0.0414   0.4814   0.8258
   3.000   0.5012   0.00647   0.00159  -0.0405   0.3524   0.8533
   3.250   0.5209   0.00753   0.00204  -0.0395   0.1839   0.8775
   3.500   0.5429   0.00831   0.00240  -0.0387   0.0760   0.8931
   3.750   0.5671   0.00871   0.00269  -0.0381   0.0404   0.9065
   4.000   0.5915   0.00900   0.00299  -0.0373   0.0306   0.9207
   4.250   0.6156   0.00916   0.00321  -0.0365   0.0270   0.9365
   4.500   0.6375   0.00961   0.00373  -0.0352   0.0215   0.9573
   4.750   0.6684   0.00976   0.00391  -0.0360   0.0201   0.9857
   5.000   0.6969   0.01006   0.00423  -0.0363   0.0183   1.0000
   5.250   0.7235   0.01045   0.00463  -0.0363   0.0169   1.0000
   5.500   0.7477   0.01122   0.00547  -0.0358   0.0153   1.0000
   5.750   0.7712   0.01208   0.00643  -0.0352   0.0147   1.0000
   6.000   0.7970   0.01254   0.00693  -0.0350   0.0143   1.0000
   6.250   0.8229   0.01295   0.00737  -0.0348   0.0136   1.0000
   6.500   0.8481   0.01346   0.00792  -0.0345   0.0128   1.0000
   6.750   0.8728   0.01405   0.00855  -0.0341   0.0121   1.0000
   7.000   0.8971   0.01471   0.00927  -0.0337   0.0116   1.0000
   7.250   0.9210   0.01544   0.01004  -0.0333   0.0112   1.0000
   7.500   0.9431   0.01660   0.01128  -0.0326   0.0107   1.0000
   7.750   0.9601   0.01984   0.01481  -0.0312   0.0101   1.0000
   8.000   0.9852   0.02002   0.01505  -0.0309   0.0098   1.0000
   8.250   1.0095   0.02050   0.01562  -0.0305   0.0093   1.0000
   8.500   1.0314   0.02174   0.01702  -0.0298   0.0089   1.0000
   8.750   1.0522   0.02313   0.01858  -0.0291   0.0085   1.0000
   9.000   1.0720   0.02456   0.02017  -0.0282   0.0081   1.0000
   9.250   1.0912   0.02587   0.02164  -0.0274   0.0078   1.0000
   9.500   1.1095   0.02715   0.02306  -0.0265   0.0076   1.0000
   9.750   1.1274   0.02825   0.02428  -0.0256   0.0074   1.0000
  10.000   1.1414   0.02993   0.02613  -0.0244   0.0071   1.0000
  10.250   1.1407   0.03397   0.03054  -0.0218   0.0069   1.0000
  10.500   1.1117   0.04119   0.03837  -0.0172   0.0068   1.0000
  10.750   1.0757   0.04646   0.04400  -0.0119   0.0067   1.0000
  11.000   1.0619   0.04940   0.04710  -0.0097   0.0068   1.0000
  11.250   1.0331   0.05454   0.05246  -0.0089   0.0067   1.0000
  11.500   1.0082   0.06017   0.05827  -0.0102   0.0067   1.0000
  11.750   0.9857   0.06658   0.06483  -0.0134   0.0068   1.0000
  12.000   0.9701   0.07299   0.07136  -0.0175   0.0068   1.0000
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