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NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A-010 10.0% (naca64a010-il)
Reynolds number: 200,000
Max Cl/Cd: 46.56 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a010-il-200000.txt
Download as CSV file: xf-naca64a010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A-010 10.0%                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6513   0.08395   0.08039  -0.0238   1.0000   0.0552
  -9.750  -0.6727   0.07701   0.07343  -0.0293   1.0000   0.0552
  -9.500  -0.6958   0.07208   0.06843  -0.0316   1.0000   0.0555
  -9.250  -0.7177   0.06849   0.06475  -0.0306   1.0000   0.0558
  -9.000  -0.7441   0.06599   0.06194  -0.0282   1.0000   0.0578
  -8.750  -0.7616   0.06554   0.06105  -0.0248   1.0000   0.0587
  -8.500  -0.7707   0.05762   0.05302  -0.0240   1.0000   0.0601
  -8.250  -0.7567   0.05359   0.04912  -0.0238   1.0000   0.0618
  -8.000  -0.7473   0.05090   0.04639  -0.0225   1.0000   0.0642
  -7.750  -0.7423   0.04877   0.04399  -0.0203   1.0000   0.0694
  -7.500  -0.7427   0.04524   0.04019  -0.0179   1.0000   0.0750
  -7.250  -0.7291   0.04286   0.03780  -0.0165   1.0000   0.0788
  -7.000  -0.7225   0.03369   0.02734  -0.0103   1.0000   0.0435
  -6.750  -0.7115   0.02846   0.02132  -0.0065   1.0000   0.0375
  -6.500  -0.6921   0.02622   0.01871  -0.0045   1.0000   0.0365
  -6.250  -0.6721   0.02402   0.01626  -0.0030   1.0000   0.0369
  -6.000  -0.6523   0.02257   0.01476  -0.0017   1.0000   0.0389
  -5.750  -0.6319   0.02135   0.01344  -0.0003   1.0000   0.0411
  -5.500  -0.6106   0.01994   0.01190   0.0011   1.0000   0.0420
  -5.250  -0.5903   0.01877   0.01064   0.0028   1.0000   0.0438
  -5.000  -0.5711   0.01785   0.00962   0.0045   1.0000   0.0456
  -4.750  -0.5560   0.01657   0.00837   0.0068   1.0000   0.0492
  -4.500  -0.5407   0.01583   0.00767   0.0090   1.0000   0.0535
  -4.250  -0.5256   0.01522   0.00699   0.0113   1.0000   0.0580
  -4.000  -0.5135   0.01436   0.00618   0.0139   1.0000   0.0648
  -3.750  -0.4997   0.01375   0.00560   0.0162   1.0000   0.0787
  -3.500  -0.4889   0.01266   0.00491   0.0188   1.0000   0.1456
  -3.250  -0.4810   0.01033   0.00460   0.0212   0.9960   0.5617
  -3.000  -0.4455   0.01017   0.00473   0.0197   0.9887   0.6584
  -2.750  -0.4091   0.01017   0.00482   0.0181   0.9815   0.7071
  -2.500  -0.3708   0.01022   0.00488   0.0162   0.9754   0.7448
  -2.250  -0.3369   0.01027   0.00499   0.0154   0.9674   0.7791
  -2.000  -0.3037   0.01041   0.00523   0.0152   0.9603   0.8142
  -1.750  -0.2663   0.01043   0.00521   0.0136   0.9540   0.8338
  -1.500  -0.2268   0.01040   0.00516   0.0114   0.9484   0.8462
  -1.250  -0.1881   0.01034   0.00508   0.0092   0.9416   0.8567
  -1.000  -0.1457   0.01027   0.00496   0.0063   0.9372   0.8669
  -0.750  -0.1124   0.01022   0.00490   0.0053   0.9279   0.8778
  -0.500  -0.0700   0.01018   0.00485   0.0025   0.9229   0.8858
  -0.250  -0.0374   0.01015   0.00482   0.0017   0.9128   0.8961
   0.000   0.0000   0.01015   0.00481   0.0000   0.9051   0.9051
   0.250   0.0374   0.01015   0.00482  -0.0017   0.8961   0.9128
   0.500   0.0699   0.01018   0.00485  -0.0025   0.8858   0.9229
   0.750   0.1124   0.01022   0.00490  -0.0053   0.8779   0.9279
   1.000   0.1457   0.01027   0.00496  -0.0063   0.8669   0.9372
   1.250   0.1880   0.01034   0.00508  -0.0092   0.8566   0.9416
   1.500   0.2269   0.01040   0.00516  -0.0114   0.8462   0.9484
   1.750   0.2663   0.01043   0.00521  -0.0136   0.8339   0.9540
   2.000   0.3037   0.01041   0.00522  -0.0152   0.8141   0.9603
   2.250   0.3369   0.01027   0.00499  -0.0154   0.7792   0.9673
   2.500   0.3708   0.01022   0.00488  -0.0162   0.7447   0.9753
   2.750   0.4092   0.01017   0.00481  -0.0181   0.7069   0.9815
   3.000   0.4457   0.01017   0.00473  -0.0197   0.6593   0.9887
   3.250   0.4810   0.01033   0.00461  -0.0212   0.5628   0.9959
   3.500   0.4892   0.01264   0.00490  -0.0189   0.1481   1.0000
   3.750   0.4997   0.01376   0.00561  -0.0162   0.0790   1.0000
   4.000   0.5136   0.01436   0.00618  -0.0139   0.0650   1.0000
   4.250   0.5257   0.01522   0.00700  -0.0113   0.0578   1.0000
   4.500   0.5409   0.01584   0.00767  -0.0090   0.0536   1.0000
   4.750   0.5559   0.01658   0.00837  -0.0068   0.0488   1.0000
   5.000   0.5713   0.01783   0.00960  -0.0046   0.0455   1.0000
   5.250   0.5904   0.01877   0.01064  -0.0028   0.0436   1.0000
   5.500   0.6107   0.01995   0.01191  -0.0012   0.0421   1.0000
   5.750   0.6319   0.02136   0.01345   0.0003   0.0409   1.0000
   6.000   0.6526   0.02263   0.01482   0.0017   0.0391   1.0000
   6.250   0.6721   0.02405   0.01629   0.0030   0.0368   1.0000
   6.500   0.6922   0.02620   0.01869   0.0045   0.0365   1.0000
   6.750   0.7114   0.02844   0.02128   0.0065   0.0372   1.0000
   7.000   0.7225   0.03373   0.02738   0.0103   0.0435   1.0000
   8.000   0.7470   0.05096   0.04646   0.0226   0.0645   1.0000
   8.250   0.7558   0.05361   0.04917   0.0239   0.0620   1.0000
   8.500   0.7697   0.05742   0.05286   0.0242   0.0602   1.0000
   8.750   0.7619   0.06558   0.06108   0.0247   0.0588   1.0000
   9.000   0.7430   0.06588   0.06186   0.0283   0.0577   1.0000
   9.250   0.7176   0.06847   0.06473   0.0306   0.0558   1.0000
   9.500   0.6950   0.07215   0.06850   0.0315   0.0553   1.0000
   9.750   0.6757   0.07677   0.07318   0.0297   0.0556   1.0000
  10.000   0.6534   0.08362   0.08007   0.0242   0.0555   1.0000
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