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NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 100,000
Max Cl/Cd: 36.23 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001064-il-100000.txt
Download as CSV file: xf-naca001064-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6430   0.09341   0.08824  -0.0111   1.0000   0.1629
  -9.250  -0.6758   0.08704   0.08198  -0.0184   1.0000   0.1696
  -9.000  -0.7322   0.08233   0.07721  -0.0212   1.0000   0.1710
  -8.750  -0.6806   0.07890   0.07388  -0.0181   1.0000   0.1799
  -8.500  -0.7583   0.07578   0.07048  -0.0191   1.0000   0.1863
  -8.000  -0.7863   0.05471   0.04821  -0.0175   1.0000   0.1143
  -7.750  -0.7920   0.04599   0.03834  -0.0123   1.0000   0.0848
  -7.500  -0.7817   0.04189   0.03402  -0.0102   1.0000   0.0837
  -7.250  -0.7721   0.03918   0.03086  -0.0073   1.0000   0.0843
  -7.000  -0.7603   0.03708   0.02826  -0.0044   1.0000   0.0852
  -6.750  -0.7452   0.03410   0.02495  -0.0023   1.0000   0.0855
  -6.500  -0.7275   0.03121   0.02179  -0.0006   1.0000   0.0865
  -6.250  -0.7079   0.02935   0.01988   0.0006   1.0000   0.0899
  -6.000  -0.6876   0.02782   0.01817   0.0020   1.0000   0.0930
  -5.750  -0.6658   0.02622   0.01631   0.0035   1.0000   0.0952
  -5.500  -0.6432   0.02489   0.01471   0.0048   1.0000   0.0980
  -5.250  -0.6202   0.02333   0.01320   0.0057   1.0000   0.1030
  -5.000  -0.5978   0.02227   0.01208   0.0068   1.0000   0.1085
  -4.750  -0.5749   0.02117   0.01090   0.0080   1.0000   0.1141
  -4.500  -0.5542   0.02004   0.00994   0.0093   1.0000   0.1225
  -4.250  -0.5350   0.01908   0.00909   0.0109   1.0000   0.1364
  -4.000  -0.5175   0.01802   0.00821   0.0129   1.0000   0.1602
  -3.750  -0.5036   0.01640   0.00723   0.0153   1.0000   0.2355
  -3.500  -0.5008   0.01382   0.00688   0.0202   1.0000   0.6074
  -3.250  -0.4806   0.01390   0.00754   0.0243   1.0000   0.7826
  -3.000  -0.4552   0.01451   0.00815   0.0272   1.0000   0.8537
  -2.750  -0.4072   0.01581   0.00929   0.0266   1.0000   0.9096
  -2.500  -0.3137   0.01697   0.01008   0.0159   1.0000   0.9365
  -2.250  -0.2065   0.01757   0.01036   0.0015   1.0000   0.9612
  -2.000  -0.1212   0.01746   0.01002  -0.0098   1.0000   0.9822
  -1.750  -0.0421   0.01690   0.00931  -0.0206   1.0000   0.9976
  -1.500  -0.0215   0.01657   0.00894  -0.0205   1.0000   1.0000
  -1.250  -0.0137   0.01635   0.00871  -0.0179   1.0000   1.0000
  -1.000  -0.0078   0.01617   0.00854  -0.0149   1.0000   1.0000
  -0.750  -0.0038   0.01605   0.00841  -0.0116   1.0000   1.0000
  -0.500  -0.0016   0.01596   0.00833  -0.0079   1.0000   1.0000
  -0.250  -0.0005   0.01592   0.00828  -0.0040   1.0000   1.0000
   0.000   0.0000   0.01590   0.00827   0.0000   1.0000   1.0000
   0.250   0.0005   0.01592   0.00828   0.0040   1.0000   1.0000
   0.500   0.0015   0.01596   0.00833   0.0079   1.0000   1.0000
   0.750   0.0038   0.01605   0.00841   0.0116   1.0000   1.0000
   1.000   0.0078   0.01617   0.00854   0.0149   1.0000   1.0000
   1.250   0.0137   0.01634   0.00871   0.0179   1.0000   1.0000
   1.500   0.0215   0.01657   0.00894   0.0205   1.0000   1.0000
   1.750   0.0420   0.01690   0.00930   0.0206   0.9976   1.0000
   2.000   0.1212   0.01746   0.01002   0.0098   0.9822   1.0000
   2.250   0.2064   0.01757   0.01035  -0.0015   0.9612   1.0000
   2.500   0.3136   0.01697   0.01008  -0.0158   0.9366   1.0000
   2.750   0.4071   0.01581   0.00928  -0.0266   0.9096   1.0000
   3.000   0.4551   0.01451   0.00815  -0.0272   0.8538   1.0000
   3.250   0.4805   0.01390   0.00754  -0.0243   0.7828   1.0000
   3.500   0.5007   0.01382   0.00688  -0.0202   0.6077   1.0000
   3.750   0.5035   0.01640   0.00723  -0.0153   0.2358   1.0000
   4.000   0.5174   0.01801   0.00821  -0.0129   0.1603   1.0000
   4.250   0.5349   0.01908   0.00909  -0.0109   0.1364   1.0000
   4.500   0.5541   0.02004   0.00994  -0.0093   0.1225   1.0000
   4.750   0.5748   0.02117   0.01090  -0.0080   0.1141   1.0000
   5.000   0.5977   0.02226   0.01208  -0.0068   0.1085   1.0000
   5.250   0.6202   0.02333   0.01320  -0.0057   0.1029   1.0000
   5.500   0.6431   0.02489   0.01471  -0.0048   0.0980   1.0000
   5.750   0.6657   0.02622   0.01631  -0.0034   0.0952   1.0000
   6.000   0.6875   0.02781   0.01816  -0.0020   0.0930   1.0000
   6.250   0.7079   0.02935   0.01988  -0.0005   0.0899   1.0000
   6.500   0.7274   0.03120   0.02179   0.0007   0.0865   1.0000
   6.750   0.7451   0.03410   0.02495   0.0023   0.0855   1.0000
   7.000   0.7602   0.03708   0.02826   0.0044   0.0852   1.0000
   7.250   0.7721   0.03918   0.03086   0.0073   0.0843   1.0000
   7.500   0.7817   0.04189   0.03402   0.0102   0.0837   1.0000
   7.750   0.7920   0.04599   0.03833   0.0123   0.0848   1.0000
   8.000   0.7863   0.05187   0.04529   0.0176   0.1014   1.0000
   8.750   0.6809   0.07892   0.07390   0.0180   0.1798   1.0000
   9.000   0.5393   0.07788   0.07300   0.0190   0.1905   1.0000
   9.250   0.6752   0.08712   0.08206   0.0181   0.1695   1.0000
   9.500   0.6439   0.09342   0.08825   0.0111   0.1628   1.0000
   9.750   0.6802   0.09500   0.08990   0.0184   0.1559   1.0000
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