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NACA 64-008A AIRFOIL (n64008a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-008A AIRFOIL (n64008a-il)
Reynolds number: 50,000
Max Cl/Cd: 19.06 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64008a-il-50000.txt
Download as CSV file: xf-n64008a-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-008A AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.6776   0.05318   0.04526  -0.0137   1.0000   0.1538
  -6.250  -0.6581   0.04768   0.03931  -0.0137   1.0000   0.1334
  -6.000  -0.6385   0.04335   0.03430  -0.0129   1.0000   0.1207
  -5.750  -0.6169   0.03981   0.02991  -0.0117   1.0000   0.1124
  -5.500  -0.5944   0.03658   0.02617  -0.0107   1.0000   0.1114
  -5.250  -0.5707   0.03411   0.02306  -0.0094   1.0000   0.1138
  -5.000  -0.5447   0.03118   0.01984  -0.0085   1.0000   0.1154
  -4.750  -0.5167   0.02860   0.01707  -0.0078   1.0000   0.1177
  -4.500  -0.4873   0.02645   0.01478  -0.0069   1.0000   0.1233
  -4.250  -0.4593   0.02459   0.01290  -0.0060   1.0000   0.1384
  -4.000  -0.4333   0.02272   0.01108  -0.0048   1.0000   0.1595
  -3.750  -0.2491   0.02188   0.01257  -0.0098   1.0000   0.9931
  -3.500  -0.2151   0.02087   0.01115  -0.0131   1.0000   1.0000
  -3.250  -0.1968   0.02014   0.01020  -0.0134   1.0000   1.0000
  -3.000  -0.1783   0.01948   0.00935  -0.0135   1.0000   1.0000
  -2.750  -0.1598   0.01888   0.00859  -0.0135   1.0000   1.0000
  -2.500  -0.1413   0.01834   0.00791  -0.0134   1.0000   1.0000
  -2.250  -0.1231   0.01785   0.00731  -0.0132   1.0000   1.0000
  -2.000  -0.1050   0.01742   0.00674  -0.0128   1.0000   1.0000
  -1.750  -0.0874   0.01703   0.00628  -0.0123   1.0000   1.0000
  -1.500  -0.0704   0.01670   0.00589  -0.0115   1.0000   1.0000
  -1.250  -0.0543   0.01641   0.00557  -0.0105   1.0000   1.0000
  -1.000  -0.0395   0.01616   0.00531  -0.0093   1.0000   1.0000
  -0.750  -0.0264   0.01597   0.00509  -0.0076   1.0000   1.0000
  -0.500  -0.0155   0.01582   0.00495  -0.0055   1.0000   1.0000
  -0.250  -0.0072   0.01573   0.00488  -0.0028   1.0000   1.0000
   0.000   0.0000   0.01570   0.00485   0.0000   1.0000   1.0000
   0.250   0.0072   0.01573   0.00488   0.0028   1.0000   1.0000
   0.500   0.0156   0.01582   0.00495   0.0054   1.0000   1.0000
   0.750   0.0264   0.01596   0.00509   0.0076   1.0000   1.0000
   1.000   0.0395   0.01616   0.00530   0.0093   1.0000   1.0000
   1.250   0.0544   0.01640   0.00556   0.0105   1.0000   1.0000
   1.500   0.0705   0.01669   0.00589   0.0115   1.0000   1.0000
   1.750   0.0875   0.01703   0.00628   0.0123   1.0000   1.0000
   2.000   0.1051   0.01741   0.00674   0.0128   1.0000   1.0000
   2.250   0.1231   0.01785   0.00730   0.0132   1.0000   1.0000
   2.500   0.1414   0.01833   0.00790   0.0134   1.0000   1.0000
   2.750   0.1599   0.01887   0.00858   0.0135   1.0000   1.0000
   3.000   0.1785   0.01947   0.00934   0.0135   1.0000   1.0000
   3.250   0.1970   0.02013   0.01019   0.0133   1.0000   1.0000
   3.500   0.2153   0.02086   0.01114   0.0131   1.0000   1.0000
   3.750   0.2495   0.02187   0.01256   0.0097   0.9930   1.0000
   4.000   0.4333   0.02273   0.01108   0.0048   0.1595   1.0000
   4.250   0.4592   0.02459   0.01290   0.0060   0.1384   1.0000
   4.500   0.4872   0.02645   0.01478   0.0069   0.1233   1.0000
   4.750   0.5166   0.02860   0.01707   0.0078   0.1177   1.0000
   5.000   0.5447   0.03118   0.01983   0.0085   0.1153   1.0000
   5.250   0.5707   0.03411   0.02306   0.0094   0.1138   1.0000
   5.500   0.5944   0.03658   0.02616   0.0107   0.1114   1.0000
   5.750   0.6169   0.03982   0.02992   0.0117   0.1124   1.0000
   6.000   0.6385   0.04335   0.03430   0.0129   0.1207   1.0000
   6.250   0.6582   0.04769   0.03932   0.0136   0.1334   1.0000
   6.500   0.6778   0.05320   0.04528   0.0137   0.1539   1.0000
   8.250   0.6249   0.10021   0.09354  -0.0334   0.3816   1.0000
   8.500   0.6488   0.10514   0.09850  -0.0316   0.3606   1.0000
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