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NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-209 (naca66209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 64.93 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66209-il-1000000-n5.txt
Download as CSV file: xf-naca66209-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7845   0.02153   0.01778  -0.0503   0.9445   0.0040
  -9.250  -0.7683   0.01933   0.01522  -0.0491   0.9361   0.0042
  -9.000  -0.7486   0.01800   0.01365  -0.0483   0.9285   0.0043
  -8.750  -0.7281   0.01677   0.01219  -0.0474   0.9219   0.0044
  -8.500  -0.7078   0.01546   0.01065  -0.0466   0.9150   0.0047
  -8.250  -0.6835   0.01506   0.01019  -0.0463   0.9097   0.0051
  -8.000  -0.6595   0.01449   0.00953  -0.0459   0.9042   0.0053
  -7.750  -0.6349   0.01410   0.00903  -0.0456   0.8990   0.0057
  -7.500  -0.6099   0.01375   0.00862  -0.0454   0.8942   0.0062
  -7.250  -0.5850   0.01331   0.00809  -0.0451   0.8890   0.0066
  -7.000  -0.5596   0.01301   0.00770  -0.0449   0.8842   0.0070
  -6.750  -0.5348   0.01251   0.00710  -0.0446   0.8796   0.0072
  -6.500  -0.5112   0.01175   0.00625  -0.0441   0.8746   0.0080
  -6.250  -0.4853   0.01152   0.00597  -0.0440   0.8704   0.0085
  -6.000  -0.4594   0.01122   0.00562  -0.0439   0.8664   0.0090
  -5.750  -0.4336   0.01089   0.00524  -0.0437   0.8622   0.0096
  -5.500  -0.4073   0.01068   0.00499  -0.0436   0.8581   0.0103
  -5.250  -0.3814   0.01038   0.00463  -0.0434   0.8543   0.0108
  -5.000  -0.3551   0.01012   0.00433  -0.0434   0.8503   0.0111
  -4.750  -0.3301   0.00961   0.00372  -0.0430   0.8460   0.0116
  -4.500  -0.3048   0.00916   0.00321  -0.0427   0.8423   0.0130
  -4.250  -0.2781   0.00894   0.00297  -0.0427   0.8390   0.0140
  -4.000  -0.2513   0.00872   0.00273  -0.0427   0.8355   0.0149
  -3.750  -0.2245   0.00850   0.00246  -0.0426   0.8320   0.0157
  -3.500  -0.1976   0.00831   0.00224  -0.0426   0.8288   0.0166
  -3.250  -0.1704   0.00816   0.00205  -0.0426   0.8257   0.0173
  -3.000  -0.1434   0.00793   0.00180  -0.0426   0.8223   0.0194
  -2.750  -0.1161   0.00777   0.00165  -0.0427   0.8188   0.0237
  -2.500  -0.0887   0.00766   0.00151  -0.0427   0.8157   0.0267
  -2.000  -0.0335   0.00744   0.00127  -0.0429   0.8102   0.0334
  -1.750  -0.0058   0.00733   0.00119  -0.0431   0.8072   0.0394
  -1.500   0.0208   0.00701   0.00107  -0.0431   0.8042   0.1050
  -1.250   0.0449   0.00623   0.00091  -0.0430   0.8012   0.3065
  -1.000   0.0655   0.00492   0.00072  -0.0425   0.7982   0.6442
  -0.750   0.0920   0.00472   0.00077  -0.0423   0.7955   0.7227
  -0.500   0.1198   0.00468   0.00079  -0.0424   0.7926   0.7466
  -0.250   0.1476   0.00466   0.00080  -0.0424   0.7890   0.7626
   0.000   0.1752   0.00466   0.00080  -0.0424   0.7807   0.7740
   0.250   0.2026   0.00468   0.00080  -0.0423   0.7681   0.7831
   0.500   0.2297   0.00470   0.00081  -0.0422   0.7565   0.7937
   0.750   0.2574   0.00473   0.00083  -0.0422   0.7445   0.8005
   1.000   0.2848   0.00477   0.00084  -0.0422   0.7294   0.8035
   1.250   0.3114   0.00486   0.00085  -0.0420   0.6998   0.8067
   1.500   0.3335   0.00531   0.00090  -0.0409   0.5916   0.8100
   1.750   0.3502   0.00640   0.00122  -0.0392   0.3966   0.8134
   2.000   0.3677   0.00748   0.00155  -0.0378   0.1979   0.8168
   2.250   0.3895   0.00817   0.00181  -0.0371   0.0768   0.8205
   2.500   0.4148   0.00849   0.00198  -0.0368   0.0385   0.8243
   2.750   0.4416   0.00864   0.00212  -0.0367   0.0315   0.8276
   3.000   0.4680   0.00881   0.00228  -0.0366   0.0272   0.8309
   3.250   0.4943   0.00899   0.00250  -0.0364   0.0231   0.8345
   3.500   0.5211   0.00913   0.00265  -0.0364   0.0220   0.8382
   3.750   0.5475   0.00931   0.00283  -0.0363   0.0191   0.8416
   4.000   0.5731   0.00954   0.00306  -0.0360   0.0155   0.8453
   4.250   0.5986   0.00981   0.00337  -0.0357   0.0142   0.8495
   4.500   0.6243   0.01005   0.00366  -0.0354   0.0137   0.8538
   4.750   0.6496   0.01031   0.00396  -0.0351   0.0132   0.8578
   5.000   0.6746   0.01059   0.00429  -0.0347   0.0126   0.8621
   5.250   0.6996   0.01090   0.00465  -0.0343   0.0121   0.8666
   5.500   0.7242   0.01122   0.00502  -0.0339   0.0116   0.8708
   5.750   0.7485   0.01154   0.00540  -0.0334   0.0111   0.8755
   6.000   0.7727   0.01190   0.00578  -0.0330   0.0103   0.8806
   6.250   0.7947   0.01251   0.00648  -0.0320   0.0096   0.8859
   6.500   0.8148   0.01336   0.00746  -0.0308   0.0091   0.8920
   6.750   0.8389   0.01371   0.00786  -0.0303   0.0089   0.8975
   7.000   0.8623   0.01406   0.00830  -0.0297   0.0086   0.9032
   7.250   0.8862   0.01439   0.00869  -0.0292   0.0082   0.9092
   7.500   0.9087   0.01487   0.00925  -0.0285   0.0078   0.9152
   7.750   0.9309   0.01539   0.00985  -0.0277   0.0075   0.9221
   8.000   0.9531   0.01582   0.01036  -0.0269   0.0071   0.9290
   8.250   0.9753   0.01619   0.01078  -0.0261   0.0067   0.9373
   8.500   0.9974   0.01645   0.01110  -0.0253   0.0064   0.9463
   8.750   1.0189   0.01685   0.01158  -0.0245   0.0061   0.9579
   9.000   1.0424   0.01769   0.01254  -0.0243   0.0056   0.9747
   9.250   1.0683   0.01828   0.01322  -0.0245   0.0054   1.0000
   9.500   1.0907   0.01884   0.01387  -0.0240   0.0051   1.0000
   9.750   1.1124   0.01949   0.01460  -0.0234   0.0048   1.0000
  10.000   1.1336   0.02018   0.01538  -0.0227   0.0045   1.0000
  10.250   1.1547   0.02077   0.01604  -0.0221   0.0042   1.0000
  10.500   1.1751   0.02145   0.01681  -0.0213   0.0040   1.0000
  10.750   1.1954   0.02204   0.01745  -0.0205   0.0038   1.0000
  11.000   1.2139   0.02290   0.01843  -0.0195   0.0036   1.0000
  11.250   1.2278   0.02437   0.02009  -0.0180   0.0033   1.0000
  11.500   1.2413   0.02578   0.02167  -0.0164   0.0032   1.0000
  11.750   1.2545   0.02704   0.02311  -0.0147   0.0031   1.0000
  12.000   1.2601   0.02887   0.02517  -0.0121   0.0031   1.0000
  12.250   1.2621   0.03090   0.02743  -0.0090   0.0030   1.0000
  12.500   1.2614   0.03306   0.02982  -0.0059   0.0030   1.0000
  12.750   1.2554   0.03576   0.03278  -0.0026   0.0029   1.0000
  13.000   1.2311   0.04047   0.03787   0.0016   0.0029   1.0000
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