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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 50,000
Max Cl/Cd: 23.38 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64206-il-50000.txt
Download as CSV file: xf-naca64206-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5586   0.10168   0.09493   0.0060   1.0000   0.2375
  -8.000  -0.5590   0.09881   0.09214   0.0058   1.0000   0.2541
  -7.750  -0.5664   0.09653   0.08997   0.0050   1.0000   0.2696
  -7.500  -0.5508   0.09237   0.08582   0.0072   1.0000   0.2947
  -7.250  -0.5425   0.08888   0.08237   0.0088   1.0000   0.3205
  -7.000  -0.5381   0.08592   0.07948   0.0105   1.0000   0.3485
  -6.750  -0.5230   0.08221   0.07579   0.0133   1.0000   0.3845
  -6.500  -0.5107   0.07908   0.07269   0.0164   1.0000   0.4267
  -6.250  -0.5058   0.07677   0.07044   0.0198   1.0000   0.4709
  -6.000  -0.4867   0.07344   0.06712   0.0236   1.0000   0.5251
  -5.750  -0.4502   0.06846   0.06199   0.0259   1.0000   0.5839
  -4.750  -0.4241   0.04158   0.03328  -0.0369   1.0000   0.1615
  -4.500  -0.3932   0.03720   0.02826  -0.0376   1.0000   0.1319
  -4.250  -0.3641   0.03371   0.02413  -0.0375   1.0000   0.1169
  -4.000  -0.3366   0.03083   0.02070  -0.0371   1.0000   0.1136
  -3.750  -0.3098   0.02842   0.01777  -0.0365   1.0000   0.1168
  -3.500  -0.2822   0.02610   0.01504  -0.0355   1.0000   0.1150
  -3.250  -0.2553   0.02410   0.01275  -0.0342   1.0000   0.1158
  -3.000  -0.2295   0.02241   0.01085  -0.0325   1.0000   0.1202
  -2.750  -0.2056   0.02085   0.00926  -0.0308   1.0000   0.1319
  -2.500  -0.1824   0.01939   0.00786  -0.0296   1.0000   0.1622
  -2.250  -0.1316   0.01460   0.00626  -0.0265   1.0000   1.0000
  -2.000  -0.1194   0.01441   0.00562  -0.0242   1.0000   1.0000
  -1.750  -0.1041   0.01428   0.00502  -0.0226   1.0000   1.0000
  -1.500  -0.0858   0.01420   0.00461  -0.0215   1.0000   1.0000
  -1.250  -0.0657   0.01416   0.00428  -0.0207   1.0000   1.0000
  -1.000  -0.0446   0.01416   0.00403  -0.0200   1.0000   1.0000
  -0.750  -0.0231   0.01419   0.00385  -0.0194   1.0000   1.0000
  -0.500  -0.0012   0.01425   0.00374  -0.0189   1.0000   1.0000
  -0.250   0.0208   0.01435   0.00365  -0.0185   1.0000   1.0000
   0.000   0.0429   0.01447   0.00365  -0.0180   1.0000   1.0000
   0.250   0.0649   0.01462   0.00371  -0.0176   1.0000   1.0000
   0.500   0.0867   0.01481   0.00383  -0.0172   1.0000   1.0000
   0.750   0.1084   0.01503   0.00402  -0.0168   1.0000   1.0000
   1.000   0.1299   0.01528   0.00426  -0.0165   1.0000   1.0000
   1.250   0.1511   0.01557   0.00458  -0.0162   1.0000   1.0000
   1.500   0.1721   0.01590   0.00494  -0.0159   1.0000   1.0000
   1.750   0.1928   0.01627   0.00536  -0.0156   1.0000   1.0000
   2.000   0.2132   0.01668   0.00586  -0.0154   1.0000   1.0000
   2.250   0.2332   0.01714   0.00643  -0.0152   1.0000   1.0000
   2.500   0.2530   0.01766   0.00707  -0.0151   1.0000   1.0000
   2.750   0.2725   0.01822   0.00779  -0.0150   1.0000   1.0000
   3.000   0.2915   0.01885   0.00868  -0.0150   1.0000   1.0000
   3.250   0.3103   0.01954   0.00958  -0.0150   1.0000   1.0000
   3.500   0.3287   0.02029   0.01058  -0.0151   1.0000   1.0000
   3.750   0.3467   0.02113   0.01169  -0.0153   1.0000   1.0000
   4.000   0.5423   0.02320   0.01149  -0.0235   0.1324   1.0000
   4.250   0.5723   0.02532   0.01363  -0.0224   0.1200   1.0000
   4.500   0.6040   0.02784   0.01612  -0.0218   0.1116   1.0000
   4.750   0.6326   0.03005   0.01865  -0.0211   0.1009   1.0000
   5.000   0.6620   0.03293   0.02191  -0.0202   0.1001   1.0000
   5.250   0.6905   0.03614   0.02580  -0.0191   0.1040   1.0000
   5.500   0.7165   0.04006   0.03015  -0.0183   0.1092   1.0000
   5.750   0.7420   0.04404   0.03510  -0.0173   0.1213   1.0000
   6.000   0.7665   0.04881   0.04083  -0.0168   0.1446   1.0000
   6.250   0.7908   0.05568   0.04879  -0.0192   0.1988   1.0000
   6.500   0.7694   0.07399   0.06819  -0.0523   0.4052   1.0000
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