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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 200,000
Max Cl/Cd: 51.34 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64206-il-200000-n5.txt
Download as CSV file: xf-naca64206-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5447   0.08462   0.08119  -0.0102   1.0000   0.0092
  -7.750  -0.5473   0.08046   0.07707  -0.0125   1.0000   0.0088
  -7.500  -0.5469   0.07557   0.07222  -0.0172   1.0000   0.0087
  -7.250  -0.5424   0.07082   0.06745  -0.0216   1.0000   0.0083
  -7.000  -0.5358   0.06543   0.06201  -0.0260   1.0000   0.0083
  -6.750  -0.5271   0.06041   0.05689  -0.0293   1.0000   0.0081
  -6.500  -0.5162   0.05549   0.05184  -0.0319   1.0000   0.0079
  -6.250  -0.5022   0.05052   0.04669  -0.0339   1.0000   0.0081
  -5.750  -0.4669   0.04076   0.03627  -0.0361   1.0000   0.0107
  -5.500  -0.4513   0.03812   0.03349  -0.0367   1.0000   0.0122
  -5.250  -0.4285   0.03273   0.02759  -0.0362   1.0000   0.0108
  -5.000  -0.4060   0.02922   0.02368  -0.0356   1.0000   0.0105
  -4.750  -0.3835   0.02619   0.02026  -0.0350   1.0000   0.0104
  -4.500  -0.3606   0.02306   0.01668  -0.0344   1.0000   0.0105
  -4.250  -0.3370   0.02031   0.01352  -0.0337   1.0000   0.0108
  -4.000  -0.3131   0.01816   0.01104  -0.0329   1.0000   0.0117
  -3.750  -0.2892   0.01703   0.00972  -0.0323   1.0000   0.0139
  -3.500  -0.2651   0.01593   0.00843  -0.0314   1.0000   0.0170
  -3.250  -0.2411   0.01456   0.00689  -0.0305   1.0000   0.0185
  -3.000  -0.2175   0.01365   0.00586  -0.0296   1.0000   0.0200
  -2.750  -0.1943   0.01260   0.00474  -0.0291   1.0000   0.0249
  -2.500  -0.1601   0.01179   0.00382  -0.0306   0.9954   0.0274
  -2.250  -0.1250   0.01124   0.00311  -0.0323   0.9897   0.0322
  -2.000  -0.0900   0.01067   0.00253  -0.0341   0.9840   0.0521
  -1.750  -0.0592   0.00857   0.00221  -0.0364   0.9791   0.5102
  -1.500  -0.0341   0.00783   0.00234  -0.0354   0.9714   0.7492
  -1.250  -0.0118   0.00762   0.00243  -0.0332   0.9624   0.8548
  -1.000   0.0171   0.00754   0.00235  -0.0328   0.9545   0.8969
  -0.750   0.0486   0.00749   0.00224  -0.0334   0.9451   0.9169
  -0.500   0.0830   0.00744   0.00211  -0.0347   0.9369   0.9351
  -0.250   0.1199   0.00739   0.00201  -0.0366   0.9289   0.9527
   0.000   0.1578   0.00734   0.00193  -0.0388   0.9197   0.9706
   0.250   0.1965   0.00729   0.00187  -0.0412   0.9101   0.9936
   0.500   0.2276   0.00730   0.00186  -0.0419   0.8984   1.0000
   0.750   0.2564   0.00734   0.00188  -0.0421   0.8859   1.0000
   1.000   0.2843   0.00738   0.00192  -0.0422   0.8730   1.0000
   1.250   0.3117   0.00744   0.00199  -0.0420   0.8599   1.0000
   1.500   0.3389   0.00751   0.00208  -0.0418   0.8464   1.0000
   1.750   0.3654   0.00759   0.00223  -0.0414   0.8292   1.0000
   2.000   0.3897   0.00768   0.00225  -0.0402   0.7929   1.0000
   2.250   0.4092   0.00797   0.00210  -0.0375   0.6865   1.0000
   2.500   0.4286   0.00865   0.00212  -0.0355   0.5362   1.0000
   2.750   0.4430   0.01064   0.00256  -0.0339   0.1884   1.0000
   3.000   0.4655   0.01182   0.00319  -0.0335   0.0532   1.0000
   3.250   0.4909   0.01248   0.00385  -0.0332   0.0363   1.0000
   3.500   0.5167   0.01308   0.00459  -0.0328   0.0315   1.0000
   3.750   0.5409   0.01400   0.00555  -0.0324   0.0247   1.0000
   4.000   0.5660   0.01475   0.00642  -0.0319   0.0228   1.0000
   4.250   0.5904   0.01584   0.00764  -0.0312   0.0206   1.0000
   4.500   0.6151   0.01715   0.00907  -0.0305   0.0183   1.0000
   4.750   0.6399   0.01817   0.01022  -0.0302   0.0144   1.0000
   5.000   0.6638   0.02108   0.01341  -0.0293   0.0129   1.0000
   5.250   0.6895   0.02310   0.01577  -0.0285   0.0122   1.0000
   5.500   0.7146   0.02536   0.01844  -0.0275   0.0108   1.0000
   5.750   0.7389   0.02720   0.02063  -0.0268   0.0085   1.0000
   6.000   0.7607   0.03048   0.02438  -0.0256   0.0079   1.0000
   6.250   0.7803   0.03437   0.02874  -0.0244   0.0076   1.0000
   6.500   0.7973   0.03887   0.03372  -0.0231   0.0076   1.0000
   6.750   0.8116   0.04390   0.03920  -0.0218   0.0077   1.0000
   7.000   0.8231   0.04922   0.04491  -0.0209   0.0079   1.0000
   7.250   0.8315   0.05463   0.05065  -0.0204   0.0082   1.0000
   7.500   0.8365   0.06009   0.05638  -0.0203   0.0085   1.0000
   7.750   0.8383   0.06544   0.06195  -0.0208   0.0087   1.0000
   8.000   0.8359   0.07086   0.06753  -0.0218   0.0090   1.0000
   8.250   0.8302   0.07612   0.07292  -0.0236   0.0092   1.0000
   8.500   0.8190   0.08103   0.07789  -0.0256   0.0093   1.0000
   8.750   0.8076   0.08722   0.08410  -0.0311   0.0094   1.0000
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