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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.04 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65209-il-1000000-n5.txt
Download as CSV file: xf-naca65209-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5750   0.14158   0.13983   0.0013   1.0000   0.0031
 -12.750  -0.5715   0.13748   0.13574  -0.0004   1.0000   0.0033
  -9.750  -0.8654   0.02263   0.01910  -0.0384   1.0000   0.0037
  -9.500  -0.8514   0.02045   0.01660  -0.0370   1.0000   0.0039
  -9.250  -0.8276   0.01878   0.01468  -0.0373   0.9955   0.0041
  -9.000  -0.7997   0.01743   0.01311  -0.0383   0.9898   0.0042
  -8.750  -0.7701   0.01639   0.01190  -0.0394   0.9844   0.0043
  -8.500  -0.7416   0.01497   0.01027  -0.0404   0.9775   0.0047
  -8.250  -0.7115   0.01429   0.00949  -0.0415   0.9702   0.0050
  -8.000  -0.6813   0.01383   0.00898  -0.0424   0.9626   0.0054
  -7.750  -0.6531   0.01343   0.00852  -0.0429   0.9531   0.0059
  -7.500  -0.6267   0.01305   0.00803  -0.0429   0.9430   0.0063
  -7.250  -0.6010   0.01267   0.00757  -0.0427   0.9333   0.0068
  -7.000  -0.5758   0.01230   0.00710  -0.0424   0.9235   0.0070
  -6.750  -0.5518   0.01163   0.00634  -0.0420   0.9134   0.0078
  -6.500  -0.5260   0.01138   0.00604  -0.0418   0.9044   0.0083
  -6.250  -0.5002   0.01113   0.00574  -0.0416   0.8955   0.0088
  -6.000  -0.4742   0.01085   0.00538  -0.0414   0.8868   0.0094
  -5.750  -0.4483   0.01054   0.00500  -0.0412   0.8786   0.0101
  -5.500  -0.4218   0.01036   0.00476  -0.0411   0.8700   0.0106
  -5.250  -0.3950   0.01019   0.00454  -0.0410   0.8620   0.0109
  -4.750  -0.3438   0.00921   0.00339  -0.0405   0.8462   0.0130
  -4.500  -0.3169   0.00904   0.00318  -0.0405   0.8385   0.0140
  -4.250  -0.2899   0.00883   0.00292  -0.0405   0.8305   0.0149
  -4.000  -0.2629   0.00861   0.00265  -0.0404   0.8233   0.0156
  -3.750  -0.2357   0.00840   0.00239  -0.0404   0.8158   0.0162
  -3.500  -0.2084   0.00824   0.00216  -0.0404   0.8087   0.0168
  -3.250  -0.1811   0.00803   0.00189  -0.0404   0.8010   0.0179
  -3.000  -0.1537   0.00784   0.00168  -0.0404   0.7940   0.0216
  -2.750  -0.1260   0.00771   0.00153  -0.0405   0.7870   0.0246
  -2.500  -0.0983   0.00761   0.00139  -0.0406   0.7805   0.0266
  -2.250  -0.0706   0.00749   0.00125  -0.0406   0.7733   0.0326
  -2.000  -0.0429   0.00738   0.00115  -0.0407   0.7667   0.0415
  -1.750  -0.0154   0.00713   0.00103  -0.0408   0.7599   0.0885
  -1.500   0.0111   0.00658   0.00088  -0.0411   0.7537   0.2215
  -1.250   0.0360   0.00552   0.00067  -0.0414   0.7469   0.4842
  -1.000   0.0622   0.00508   0.00066  -0.0413   0.7405   0.6234
  -0.750   0.0900   0.00498   0.00066  -0.0414   0.7339   0.6609
  -0.250   0.1461   0.00494   0.00066  -0.0416   0.7209   0.6962
   0.000   0.1740   0.00493   0.00068  -0.0416   0.7142   0.7146
   0.250   0.2023   0.00493   0.00070  -0.0418   0.7076   0.7233
   0.500   0.2304   0.00495   0.00071  -0.0419   0.7002   0.7300
   0.750   0.2585   0.00497   0.00073  -0.0420   0.6899   0.7371
   1.000   0.2859   0.00505   0.00075  -0.0419   0.6674   0.7436
   1.250   0.3131   0.00515   0.00079  -0.0418   0.6433   0.7507
   1.500   0.3399   0.00529   0.00083  -0.0417   0.6053   0.7574
   1.750   0.3654   0.00560   0.00090  -0.0413   0.5370   0.7645
   2.000   0.3857   0.00665   0.00120  -0.0405   0.3397   0.7717
   2.250   0.4070   0.00766   0.00155  -0.0398   0.1626   0.7795
   2.500   0.4318   0.00818   0.00178  -0.0395   0.0806   0.7867
   2.750   0.4578   0.00850   0.00198  -0.0394   0.0419   0.7943
   3.000   0.4846   0.00868   0.00214  -0.0393   0.0314   0.8018
   3.250   0.5115   0.00885   0.00233  -0.0392   0.0260   0.8101
   3.500   0.5382   0.00903   0.00253  -0.0391   0.0216   0.8180
   4.000   0.5916   0.00939   0.00295  -0.0389   0.0174   0.8341
   4.250   0.6176   0.00965   0.00325  -0.0386   0.0148   0.8425
   4.500   0.6433   0.00996   0.00363  -0.0383   0.0136   0.8516
   4.750   0.6691   0.01020   0.00393  -0.0380   0.0133   0.8601
   5.000   0.6947   0.01048   0.00427  -0.0377   0.0130   0.8691
   5.250   0.7197   0.01078   0.00465  -0.0373   0.0126   0.8790
   5.500   0.7444   0.01109   0.00505  -0.0368   0.0122   0.8891
   5.750   0.7687   0.01144   0.00547  -0.0362   0.0117   0.8996
   6.250   0.8171   0.01201   0.00614  -0.0351   0.0105   0.9220
   6.500   0.8402   0.01235   0.00654  -0.0343   0.0100   0.9346
   6.750   0.8618   0.01285   0.00713  -0.0333   0.0094   0.9496
   7.000   0.8846   0.01365   0.00805  -0.0327   0.0087   0.9720
   7.250   0.9131   0.01398   0.00842  -0.0332   0.0084   1.0000
   7.500   0.9379   0.01440   0.00889  -0.0329   0.0081   1.0000
   7.750   0.9622   0.01489   0.00944  -0.0326   0.0077   1.0000
   8.000   0.9864   0.01539   0.01000  -0.0322   0.0073   1.0000
   8.250   1.0110   0.01579   0.01043  -0.0320   0.0068   1.0000
   8.500   1.0353   0.01620   0.01090  -0.0317   0.0065   1.0000
   8.750   1.0599   0.01651   0.01123  -0.0315   0.0061   1.0000
   9.000   1.0832   0.01704   0.01178  -0.0311   0.0056   1.0000
   9.250   1.1057   0.01769   0.01251  -0.0306   0.0053   1.0000
   9.500   1.1283   0.01829   0.01320  -0.0301   0.0051   1.0000
   9.750   1.1500   0.01901   0.01402  -0.0294   0.0048   1.0000
  10.000   1.1719   0.01965   0.01474  -0.0289   0.0045   1.0000
  10.250   1.1932   0.02035   0.01552  -0.0282   0.0043   1.0000
  10.500   1.2147   0.02095   0.01619  -0.0276   0.0040   1.0000
  10.750   1.2356   0.02160   0.01692  -0.0270   0.0038   1.0000
  11.000   1.2550   0.02245   0.01785  -0.0261   0.0036   1.0000
  11.250   1.2711   0.02370   0.01925  -0.0249   0.0033   1.0000
  11.500   1.2852   0.02515   0.02089  -0.0234   0.0032   1.0000
  11.750   1.2983   0.02659   0.02251  -0.0219   0.0031   1.0000
  12.000   1.3114   0.02789   0.02397  -0.0204   0.0030   1.0000
  12.250   1.3185   0.02960   0.02589  -0.0182   0.0030   1.0000
  12.500   1.3213   0.03132   0.02779  -0.0154   0.0029   1.0000
  12.750   1.3194   0.03337   0.03006  -0.0123   0.0028   1.0000
  13.000   1.3179   0.03539   0.03226  -0.0098   0.0028   1.0000
  13.250   1.3129   0.03784   0.03491  -0.0074   0.0027   1.0000
  13.500   1.3022   0.04100   0.03829  -0.0053   0.0026   1.0000
  13.750   1.2815   0.04545   0.04301  -0.0037   0.0026   1.0000
  14.000   1.2582   0.05065   0.04845  -0.0032   0.0026   1.0000
  14.250   1.2067   0.06041   0.05857  -0.0053   0.0027   1.0000
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