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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 500,000
Max Cl/Cd: 71.32 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65209-il-500000.txt
Download as CSV file: xf-naca65209-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5860   0.05117   0.04835  -0.0420   1.0000   0.0168
  -7.500  -0.5937   0.04627   0.04330  -0.0404   1.0000   0.0173
  -7.250  -0.5904   0.04421   0.04121  -0.0385   1.0000   0.0178
  -7.000  -0.5908   0.04230   0.03922  -0.0354   1.0000   0.0181
  -6.750  -0.5696   0.03963   0.03640  -0.0369   0.9973   0.0192
  -6.500  -0.5397   0.03653   0.03304  -0.0394   0.9938   0.0215
  -6.250  -0.5018   0.03665   0.03277  -0.0402   0.9898   0.0243
  -5.500  -0.4199   0.01976   0.01447  -0.0446   0.9776   0.0200
  -5.250  -0.3869   0.01737   0.01177  -0.0457   0.9740   0.0202
  -5.000  -0.3525   0.01616   0.01037  -0.0471   0.9707   0.0219
  -4.750  -0.3214   0.01467   0.00871  -0.0477   0.9653   0.0226
  -4.500  -0.2907   0.01369   0.00762  -0.0483   0.9592   0.0235
  -4.250  -0.2601   0.01317   0.00701  -0.0488   0.9532   0.0243
  -4.000  -0.2369   0.01141   0.00519  -0.0481   0.9445   0.0268
  -3.750  -0.2117   0.01077   0.00449  -0.0477   0.9359   0.0287
  -3.500  -0.1861   0.01029   0.00395  -0.0472   0.9281   0.0309
  -3.250  -0.1610   0.00989   0.00349  -0.0467   0.9191   0.0335
  -3.000  -0.1355   0.00949   0.00300  -0.0462   0.9114   0.0373
  -2.750  -0.1100   0.00910   0.00257  -0.0458   0.9027   0.0449
  -2.500  -0.0843   0.00866   0.00221  -0.0454   0.8947   0.0778
  -2.250  -0.0669   0.00645   0.00178  -0.0449   0.8865   0.5712
  -2.000  -0.0418   0.00621   0.00179  -0.0443   0.8783   0.6605
  -1.500   0.0099   0.00611   0.00184  -0.0431   0.8631   0.7437
  -1.250   0.0359   0.00613   0.00187  -0.0424   0.8565   0.7687
  -1.000   0.0624   0.00615   0.00191  -0.0420   0.8484   0.7880
  -0.750   0.0890   0.00618   0.00192  -0.0416   0.8417   0.8024
  -0.500   0.1161   0.00617   0.00191  -0.0414   0.8340   0.8102
  -0.250   0.1438   0.00619   0.00188  -0.0413   0.8274   0.8184
   0.000   0.1710   0.00618   0.00189  -0.0411   0.8197   0.8257
   0.250   0.1985   0.00620   0.00189  -0.0410   0.8131   0.8336
   0.500   0.2257   0.00621   0.00192  -0.0409   0.8055   0.8414
   0.750   0.2529   0.00623   0.00194  -0.0407   0.7989   0.8491
   1.000   0.2801   0.00624   0.00198  -0.0406   0.7913   0.8574
   1.250   0.3069   0.00627   0.00203  -0.0403   0.7840   0.8651
   1.750   0.3588   0.00628   0.00204  -0.0392   0.7574   0.8818
   2.000   0.3840   0.00627   0.00204  -0.0384   0.7374   0.8907
   2.250   0.4081   0.00630   0.00200  -0.0374   0.7067   0.9001
   2.500   0.4317   0.00637   0.00203  -0.0363   0.6756   0.9090
   2.750   0.4554   0.00646   0.00207  -0.0353   0.6401   0.9190
   3.000   0.4771   0.00669   0.00212  -0.0339   0.5797   0.9302
   3.250   0.4871   0.00797   0.00242  -0.0307   0.3425   0.9444
   3.500   0.4967   0.00986   0.00311  -0.0282   0.0604   0.9613
   3.750   0.5256   0.01041   0.00360  -0.0286   0.0388   0.9749
   4.000   0.5599   0.01087   0.00411  -0.0303   0.0328   0.9876
   4.250   0.5877   0.01176   0.00506  -0.0308   0.0282   1.0000
   4.500   0.6131   0.01221   0.00554  -0.0306   0.0266   1.0000
   4.750   0.6376   0.01285   0.00624  -0.0302   0.0251   1.0000
   5.000   0.6617   0.01357   0.00701  -0.0298   0.0237   1.0000
   5.250   0.6856   0.01442   0.00790  -0.0292   0.0226   1.0000
   5.500   0.7096   0.01532   0.00881  -0.0288   0.0213   1.0000
   5.750   0.7321   0.01730   0.01084  -0.0281   0.0198   1.0000
   6.000   0.7570   0.01971   0.01343  -0.0276   0.0192   1.0000
   6.250   0.7826   0.02074   0.01461  -0.0272   0.0188   1.0000
   6.500   0.8073   0.02255   0.01664  -0.0266   0.0184   1.0000
   6.750   0.8312   0.02433   0.01866  -0.0259   0.0178   1.0000
   7.000   0.8539   0.02631   0.02090  -0.0250   0.0170   1.0000
   7.250   0.8708   0.03037   0.02540  -0.0232   0.0177   1.0000
  11.000   0.6775   0.10293   0.10101  -0.0217   0.0193   1.0000
  11.250   0.6695   0.11103   0.10912  -0.0262   0.0193   1.0000
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