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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.93 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64209-il-1000000-n5.txt
Download as CSV file: xf-naca64209-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.9172   0.03330   0.03063  -0.0415   1.0000   0.0038
 -10.500  -0.9243   0.02672   0.02349  -0.0400   1.0000   0.0040
 -10.250  -0.9116   0.02411   0.02057  -0.0392   1.0000   0.0041
 -10.000  -0.8949   0.02222   0.01845  -0.0385   1.0000   0.0042
  -9.750  -0.8761   0.02068   0.01669  -0.0379   1.0000   0.0043
  -9.500  -0.8548   0.01967   0.01553  -0.0374   1.0000   0.0044
  -9.250  -0.8357   0.01816   0.01384  -0.0367   1.0000   0.0046
  -9.000  -0.8140   0.01724   0.01279  -0.0362   1.0000   0.0048
  -8.750  -0.7915   0.01651   0.01198  -0.0357   1.0000   0.0049
  -8.500  -0.7691   0.01579   0.01117  -0.0351   1.0000   0.0051
  -8.250  -0.7410   0.01505   0.01031  -0.0357   0.9961   0.0054
  -8.000  -0.7103   0.01433   0.00949  -0.0368   0.9892   0.0058
  -7.750  -0.6787   0.01366   0.00872  -0.0381   0.9816   0.0061
  -7.500  -0.6462   0.01312   0.00808  -0.0396   0.9734   0.0065
  -7.000  -0.5858   0.01191   0.00669  -0.0413   0.9501   0.0071
  -6.500  -0.5342   0.01094   0.00552  -0.0410   0.9225   0.0079
  -6.250  -0.5087   0.01058   0.00507  -0.0407   0.9093   0.0082
  -6.000  -0.4829   0.01025   0.00465  -0.0404   0.8971   0.0086
  -5.750  -0.4569   0.00995   0.00426  -0.0402   0.8855   0.0090
  -5.500  -0.4307   0.00967   0.00388  -0.0399   0.8744   0.0093
  -5.250  -0.4041   0.00944   0.00356  -0.0398   0.8635   0.0097
  -5.000  -0.3772   0.00924   0.00330  -0.0397   0.8527   0.0100
  -4.750  -0.3501   0.00906   0.00306  -0.0396   0.8424   0.0103
  -4.500  -0.3230   0.00889   0.00285  -0.0396   0.8325   0.0106
  -4.250  -0.2957   0.00872   0.00264  -0.0395   0.8225   0.0113
  -4.000  -0.2681   0.00864   0.00261  -0.0396   0.8131   0.0122
  -3.750  -0.2407   0.00852   0.00246  -0.0396   0.8039   0.0173
  -3.500  -0.2132   0.00836   0.00223  -0.0396   0.7940   0.0184
  -3.250  -0.1854   0.00827   0.00209  -0.0396   0.7847   0.0193
  -3.000  -0.1577   0.00822   0.00201  -0.0397   0.7758   0.0199
  -2.750  -0.1296   0.00824   0.00203  -0.0397   0.7666   0.0203
  -2.500  -0.1018   0.00815   0.00193  -0.0398   0.7579   0.0208
  -2.250  -0.0742   0.00802   0.00177  -0.0399   0.7485   0.0215
  -2.000  -0.0463   0.00795   0.00170  -0.0399   0.7390   0.0222
  -1.750  -0.0184   0.00788   0.00160  -0.0400   0.7301   0.0227
  -1.500   0.0095   0.00782   0.00154  -0.0401   0.7212   0.0238
  -1.250   0.0376   0.00778   0.00150  -0.0402   0.7130   0.0251
  -1.000   0.0655   0.00771   0.00141  -0.0403   0.7046   0.0256
  -0.750   0.0935   0.00760   0.00129  -0.0404   0.6958   0.0257
  -0.500   0.1215   0.00752   0.00118  -0.0405   0.6874   0.0257
  -0.250   0.1496   0.00744   0.00110  -0.0405   0.6788   0.0259
   0.000   0.1777   0.00738   0.00103  -0.0406   0.6713   0.0260
   0.250   0.2058   0.00733   0.00097  -0.0407   0.6629   0.0263
   0.500   0.2339   0.00730   0.00094  -0.0408   0.6528   0.0266
   0.750   0.2618   0.00729   0.00091  -0.0409   0.6405   0.0269
   1.000   0.2893   0.00734   0.00088  -0.0408   0.6167   0.0280
   1.250   0.3165   0.00742   0.00086  -0.0408   0.5859   0.0297
   1.500   0.3432   0.00759   0.00088  -0.0406   0.5398   0.0313
   1.750   0.3699   0.00777   0.00092  -0.0405   0.4946   0.0328
   2.000   0.3960   0.00808   0.00101  -0.0404   0.4283   0.0348
   2.250   0.4191   0.00765   0.00119  -0.0408   0.2968   0.4906
   2.500   0.4428   0.00814   0.00149  -0.0406   0.1725   0.5877
   2.750   0.4680   0.00852   0.00174  -0.0405   0.0964   0.6377
   3.000   0.4941   0.00880   0.00197  -0.0404   0.0526   0.6784
   3.250   0.5208   0.00895   0.00217  -0.0403   0.0365   0.7153
   3.500   0.5477   0.00906   0.00236  -0.0402   0.0311   0.7437
   3.750   0.5744   0.00919   0.00258  -0.0401   0.0256   0.7738
   4.000   0.6007   0.00926   0.00279  -0.0398   0.0238   0.8136
   4.250   0.6270   0.00944   0.00303  -0.0395   0.0201   0.8340
   4.500   0.6533   0.00967   0.00328  -0.0393   0.0166   0.8450
   4.750   0.6797   0.00986   0.00353  -0.0391   0.0154   0.8564
   5.000   0.7057   0.01009   0.00381  -0.0388   0.0141   0.8685
   5.250   0.7312   0.01035   0.00411  -0.0384   0.0130   0.8816
   5.500   0.7559   0.01067   0.00450  -0.0378   0.0118   0.8960
   5.750   0.7793   0.01111   0.00506  -0.0370   0.0111   0.9119
   6.000   0.8028   0.01141   0.00545  -0.0362   0.0110   0.9294
   6.250   0.8259   0.01171   0.00584  -0.0353   0.0108   0.9507
   6.500   0.8544   0.01206   0.00627  -0.0357   0.0106   1.0000
   6.750   0.8803   0.01241   0.00665  -0.0355   0.0102   1.0000
   7.000   0.9058   0.01282   0.00711  -0.0353   0.0097   1.0000
   7.250   0.9310   0.01326   0.00759  -0.0351   0.0094   1.0000
   7.500   0.9560   0.01371   0.00808  -0.0348   0.0090   1.0000
   7.750   0.9811   0.01412   0.00852  -0.0346   0.0086   1.0000
   8.000   1.0059   0.01458   0.00900  -0.0343   0.0081   1.0000
   8.250   1.0279   0.01545   0.00995  -0.0337   0.0074   1.0000
   8.500   1.0514   0.01607   0.01065  -0.0332   0.0072   1.0000
   8.750   1.0756   0.01656   0.01120  -0.0329   0.0070   1.0000
   9.000   1.0993   0.01708   0.01179  -0.0325   0.0067   1.0000
   9.250   1.1227   0.01765   0.01244  -0.0321   0.0064   1.0000
   9.500   1.1454   0.01830   0.01318  -0.0316   0.0061   1.0000
   9.750   1.1682   0.01888   0.01382  -0.0311   0.0058   1.0000
  10.000   1.1907   0.01947   0.01448  -0.0306   0.0055   1.0000
  10.250   1.2139   0.01991   0.01495  -0.0302   0.0052   1.0000
  10.500   1.2362   0.02045   0.01552  -0.0297   0.0050   1.0000
  10.750   1.2551   0.02146   0.01664  -0.0288   0.0046   1.0000
  11.000   1.2757   0.02214   0.01741  -0.0281   0.0045   1.0000
  11.250   1.2948   0.02298   0.01836  -0.0273   0.0043   1.0000
  11.500   1.3128   0.02390   0.01940  -0.0263   0.0041   1.0000
  11.750   1.3296   0.02490   0.02051  -0.0252   0.0040   1.0000
  12.000   1.3447   0.02599   0.02173  -0.0239   0.0038   1.0000
  12.250   1.3597   0.02697   0.02282  -0.0226   0.0037   1.0000
  12.500   1.3726   0.02804   0.02401  -0.0211   0.0035   1.0000
  12.750   1.3818   0.02907   0.02514  -0.0190   0.0034   1.0000
  13.000   1.3857   0.03043   0.02663  -0.0165   0.0033   1.0000
  13.250   1.3921   0.03161   0.02790  -0.0145   0.0032   1.0000
  13.500   1.3950   0.03317   0.02958  -0.0125   0.0031   1.0000
  13.750   1.3957   0.03502   0.03156  -0.0107   0.0030   1.0000
  14.000   1.3942   0.03720   0.03388  -0.0092   0.0029   1.0000
  14.250   1.3887   0.03993   0.03678  -0.0080   0.0029   1.0000
  14.500   1.3825   0.04294   0.03994  -0.0074   0.0028   1.0000
  14.750   1.3694   0.04700   0.04419  -0.0074   0.0028   1.0000
  15.000   1.3538   0.05175   0.04913  -0.0083   0.0027   1.0000
  15.250   1.3353   0.05738   0.05495  -0.0103   0.0027   1.0000
  15.500   1.3162   0.06373   0.06148  -0.0133   0.0027   1.0000
  15.750   1.2896   0.07209   0.07003  -0.0180   0.0028   1.0000
  16.000   1.2552   0.08345   0.08159  -0.0254   0.0028   1.0000
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