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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 500,000
Max Cl/Cd: 63.43 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63209-il-500000-n5.txt
Download as CSV file: xf-naca63209-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6513   0.07623   0.07404  -0.0207   1.0000   0.0063
  -9.750  -0.6976   0.05692   0.05465  -0.0376   1.0000   0.0060
  -9.250  -0.7966   0.02976   0.02601  -0.0392   1.0000   0.0062
  -9.000  -0.7874   0.02592   0.02169  -0.0384   1.0000   0.0066
  -8.750  -0.7660   0.02521   0.02090  -0.0382   1.0000   0.0069
  -8.500  -0.7445   0.02440   0.01997  -0.0379   1.0000   0.0072
  -8.250  -0.7237   0.02317   0.01857  -0.0375   1.0000   0.0075
  -8.000  -0.7038   0.02143   0.01656  -0.0368   1.0000   0.0079
  -7.750  -0.6830   0.01984   0.01473  -0.0362   1.0000   0.0084
  -7.500  -0.6618   0.01844   0.01309  -0.0354   1.0000   0.0089
  -7.250  -0.6399   0.01735   0.01182  -0.0347   1.0000   0.0094
  -7.000  -0.6170   0.01629   0.01059  -0.0341   0.9991   0.0098
  -6.750  -0.5856   0.01531   0.00951  -0.0356   0.9923   0.0107
  -6.500  -0.5527   0.01488   0.00904  -0.0371   0.9852   0.0116
  -6.250  -0.5206   0.01418   0.00825  -0.0383   0.9770   0.0125
  -6.000  -0.4887   0.01344   0.00740  -0.0395   0.9679   0.0132
  -5.750  -0.4568   0.01283   0.00669  -0.0406   0.9582   0.0140
  -5.500  -0.4265   0.01206   0.00581  -0.0415   0.9472   0.0150
  -5.250  -0.3976   0.01153   0.00523  -0.0420   0.9353   0.0164
  -4.750  -0.3437   0.01076   0.00431  -0.0418   0.9104   0.0186
  -4.500  -0.3172   0.01043   0.00389  -0.0415   0.8985   0.0198
  -4.250  -0.2906   0.01019   0.00357  -0.0413   0.8871   0.0211
  -4.000  -0.2642   0.00979   0.00309  -0.0411   0.8761   0.0241
  -3.750  -0.2375   0.00954   0.00279  -0.0409   0.8653   0.0276
  -3.500  -0.2104   0.00936   0.00253  -0.0407   0.8544   0.0310
  -3.250  -0.1832   0.00913   0.00226  -0.0406   0.8439   0.0388
  -3.000  -0.1561   0.00891   0.00205  -0.0405   0.8338   0.0536
  -2.750  -0.1293   0.00851   0.00183  -0.0406   0.8235   0.1091
  -2.500  -0.1030   0.00779   0.00157  -0.0408   0.8132   0.2408
  -2.250  -0.0766   0.00715   0.00135  -0.0410   0.8034   0.3780
  -2.000  -0.0496   0.00682   0.00125  -0.0411   0.7937   0.4618
  -1.750  -0.0225   0.00654   0.00121  -0.0411   0.7836   0.5407
  -1.500   0.0048   0.00638   0.00119  -0.0410   0.7741   0.5964
  -1.250   0.0319   0.00627   0.00119  -0.0408   0.7646   0.6438
  -1.000   0.0598   0.00624   0.00118  -0.0407   0.7548   0.6651
  -0.500   0.1156   0.00624   0.00114  -0.0406   0.7361   0.6931
  -0.250   0.1436   0.00623   0.00114  -0.0406   0.7263   0.7040
   0.000   0.1716   0.00624   0.00114  -0.0406   0.7167   0.7146
   0.250   0.1996   0.00627   0.00116  -0.0405   0.7072   0.7251
   0.500   0.2276   0.00628   0.00118  -0.0405   0.6970   0.7355
   0.750   0.2555   0.00630   0.00121  -0.0405   0.6869   0.7457
   1.000   0.2833   0.00634   0.00125  -0.0404   0.6763   0.7558
   1.250   0.3111   0.00638   0.00130  -0.0404   0.6642   0.7665
   1.500   0.3386   0.00643   0.00135  -0.0402   0.6496   0.7768
   1.750   0.3658   0.00650   0.00141  -0.0400   0.6280   0.7873
   2.000   0.3922   0.00665   0.00147  -0.0397   0.5906   0.7981
   2.250   0.4182   0.00686   0.00154  -0.0393   0.5442   0.8094
   2.500   0.4441   0.00708   0.00164  -0.0389   0.4986   0.8206
   2.750   0.4694   0.00740   0.00179  -0.0385   0.4404   0.8319
   3.000   0.4935   0.00793   0.00202  -0.0381   0.3528   0.8436
   3.250   0.5150   0.00893   0.00242  -0.0374   0.2061   0.8558
   3.500   0.5378   0.00969   0.00279  -0.0369   0.1090   0.8686
   3.750   0.5616   0.01019   0.00311  -0.0363   0.0588   0.8821
   4.000   0.5861   0.01050   0.00339  -0.0357   0.0406   0.8962
   4.250   0.6104   0.01073   0.00366  -0.0350   0.0327   0.9118
   4.500   0.6341   0.01101   0.00396  -0.0341   0.0265   0.9297
   5.000   0.6904   0.01155   0.00462  -0.0344   0.0201   1.0000
   5.250   0.7163   0.01207   0.00517  -0.0343   0.0176   1.0000
   5.500   0.7423   0.01256   0.00572  -0.0341   0.0165   1.0000
   5.750   0.7684   0.01298   0.00619  -0.0340   0.0156   1.0000
   6.000   0.7939   0.01350   0.00676  -0.0338   0.0149   1.0000
   6.250   0.8190   0.01406   0.00740  -0.0335   0.0143   1.0000
   6.500   0.8438   0.01466   0.00806  -0.0332   0.0137   1.0000
   6.750   0.8683   0.01528   0.00873  -0.0329   0.0132   1.0000
   7.000   0.8927   0.01589   0.00938  -0.0326   0.0125   1.0000
   7.250   0.9144   0.01699   0.01056  -0.0319   0.0115   1.0000
   7.500   0.9375   0.01788   0.01155  -0.0314   0.0111   1.0000
   7.750   0.9608   0.01871   0.01250  -0.0309   0.0108   1.0000
   8.000   0.9837   0.01964   0.01355  -0.0303   0.0103   1.0000
   8.250   1.0062   0.02064   0.01468  -0.0298   0.0099   1.0000
   8.500   1.0289   0.02148   0.01563  -0.0293   0.0093   1.0000
   8.750   1.0516   0.02220   0.01643  -0.0289   0.0088   1.0000
   9.000   1.0741   0.02281   0.01711  -0.0285   0.0083   1.0000
   9.250   1.0944   0.02386   0.01826  -0.0278   0.0079   1.0000
   9.500   1.1093   0.02615   0.02079  -0.0266   0.0075   1.0000
   9.750   1.1275   0.02755   0.02244  -0.0257   0.0073   1.0000
  10.000   1.1432   0.02932   0.02448  -0.0245   0.0070   1.0000
  10.250   1.1557   0.03148   0.02693  -0.0231   0.0067   1.0000
  10.500   1.1635   0.03413   0.02990  -0.0214   0.0064   1.0000
  10.750   1.1689   0.03666   0.03272  -0.0196   0.0061   1.0000
  11.000   1.1704   0.03915   0.03547  -0.0176   0.0058   1.0000
  11.250   1.1663   0.04136   0.03789  -0.0148   0.0057   1.0000
  11.500   1.1603   0.04369   0.04039  -0.0126   0.0055   1.0000
  11.750   1.1570   0.04583   0.04267  -0.0113   0.0054   1.0000
  12.000   1.1570   0.04777   0.04470  -0.0107   0.0053   1.0000
  12.250   1.1238   0.05447   0.05173  -0.0113   0.0053   1.0000
  12.500   1.1413   0.05447   0.05170  -0.0115   0.0052   1.0000
  12.750   1.1207   0.06044   0.05787  -0.0138   0.0052   1.0000
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