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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 77.77 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65206-il-1000000.txt
Download as CSV file: xf-naca65206-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5322   0.08537   0.08375  -0.0133   1.0000   0.0052
  -8.000  -0.5320   0.08147   0.07986  -0.0156   1.0000   0.0052
  -7.750  -0.5350   0.07756   0.07599  -0.0184   1.0000   0.0052
  -7.500  -0.5320   0.07247   0.07089  -0.0242   1.0000   0.0052
  -7.250  -0.5264   0.06769   0.06607  -0.0279   1.0000   0.0052
  -7.000  -0.5190   0.06303   0.06135  -0.0308   1.0000   0.0052
  -6.750  -0.5100   0.05844   0.05667  -0.0329   1.0000   0.0052
  -6.500  -0.4995   0.05386   0.05200  -0.0343   1.0000   0.0052
  -6.250  -0.4877   0.04947   0.04749  -0.0351   1.0000   0.0052
  -6.000  -0.4748   0.04501   0.04289  -0.0354   1.0000   0.0052
  -5.750  -0.4704   0.03657   0.03412  -0.0354   1.0000   0.0055
  -5.500  -0.4588   0.03358   0.03096  -0.0347   1.0000   0.0061
  -5.250  -0.4443   0.03196   0.02924  -0.0336   1.0000   0.0067
  -3.750  -0.2473   0.01272   0.00808  -0.0409   0.9861   0.0084
  -3.500  -0.2141   0.01027   0.00536  -0.0417   0.9841   0.0083
  -3.250  -0.1799   0.00948   0.00450  -0.0430   0.9821   0.0099
  -3.000  -0.1503   0.00832   0.00323  -0.0435   0.9766   0.0116
  -2.750  -0.1190   0.00768   0.00254  -0.0445   0.9715   0.0140
  -2.500  -0.0879   0.00734   0.00217  -0.0452   0.9657   0.0174
  -2.250  -0.0590   0.00710   0.00186  -0.0455   0.9578   0.0190
  -2.000  -0.0311   0.00691   0.00164  -0.0455   0.9493   0.0197
  -1.750  -0.0037   0.00648   0.00110  -0.0453   0.9405   0.0301
  -1.500   0.0221   0.00575   0.00086  -0.0452   0.9303   0.2001
  -1.250   0.0459   0.00444   0.00070  -0.0453   0.9200   0.5782
  -1.000   0.0716   0.00412   0.00069  -0.0449   0.9102   0.6866
  -0.750   0.0966   0.00390   0.00071  -0.0442   0.9003   0.7753
  -0.500   0.1216   0.00380   0.00074  -0.0434   0.8897   0.8273
  -0.250   0.1472   0.00376   0.00076  -0.0428   0.8789   0.8556
   0.000   0.1726   0.00375   0.00077  -0.0421   0.8681   0.8783
   0.250   0.1987   0.00376   0.00078  -0.0416   0.8562   0.8915
   0.500   0.2243   0.00379   0.00079  -0.0410   0.8394   0.9041
   0.750   0.2492   0.00384   0.00078  -0.0402   0.8151   0.9166
   1.250   0.2974   0.00400   0.00078  -0.0383   0.7512   0.9421
   1.500   0.3197   0.00419   0.00077  -0.0369   0.6882   0.9565
   1.750   0.3453   0.00444   0.00080  -0.0364   0.6194   0.9722
   2.000   0.3728   0.00552   0.00103  -0.0371   0.3797   0.9912
   2.250   0.3944   0.00716   0.00146  -0.0370   0.0598   1.0000
   2.500   0.4209   0.00766   0.00187  -0.0368   0.0232   1.0000
   2.750   0.4484   0.00785   0.00207  -0.0369   0.0211   1.0000
   3.000   0.4755   0.00817   0.00242  -0.0368   0.0168   1.0000
   3.250   0.5008   0.00892   0.00327  -0.0363   0.0138   1.0000
   3.500   0.5235   0.01026   0.00478  -0.0354   0.0130   1.0000
   3.750   0.5512   0.01036   0.00489  -0.0355   0.0124   1.0000
   4.000   0.5777   0.01078   0.00535  -0.0353   0.0111   1.0000
   4.250   0.6042   0.01122   0.00582  -0.0351   0.0093   1.0000
   4.500   0.6303   0.01173   0.00636  -0.0349   0.0082   1.0000
   4.750   0.6553   0.01265   0.00734  -0.0344   0.0074   1.0000
   5.000   0.6774   0.01588   0.01093  -0.0331   0.0062   1.0000
   5.250   0.7040   0.01666   0.01184  -0.0327   0.0054   1.0000
   5.500   0.7258   0.02149   0.01721  -0.0307   0.0054   1.0000
   9.000   0.6955   0.08850   0.08716  -0.0330   0.0064   1.0000
   9.250   0.6903   0.09474   0.09340  -0.0361   0.0064   1.0000
   9.500   0.6868   0.10076   0.09942  -0.0389   0.0064   1.0000
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