Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 100,000
Max Cl/Cd: 31.73 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001064-il-100000-n5.txt
Download as CSV file: xf-naca001064-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7444   0.08645   0.08112  -0.0258   1.0000   0.0330
 -11.500  -0.7681   0.07778   0.07238  -0.0320   1.0000   0.0328
 -11.250  -0.7927   0.07103   0.06550  -0.0359   1.0000   0.0326
 -11.000  -0.8174   0.06564   0.05994  -0.0372   1.0000   0.0325
 -10.750  -0.8415   0.06121   0.05530  -0.0361   1.0000   0.0325
 -10.500  -0.8645   0.05741   0.05122  -0.0331   1.0000   0.0327
 -10.250  -0.8831   0.05348   0.04688  -0.0298   1.0000   0.0331
 -10.000  -0.8839   0.05067   0.04398  -0.0278   1.0000   0.0339
  -9.750  -0.8777   0.04895   0.04218  -0.0261   1.0000   0.0351
  -9.500  -0.8723   0.04692   0.03997  -0.0240   1.0000   0.0364
  -9.250  -0.8690   0.04423   0.03697  -0.0215   1.0000   0.0375
  -9.000  -0.8649   0.04128   0.03362  -0.0189   1.0000   0.0387
  -8.750  -0.8579   0.03869   0.03057  -0.0162   1.0000   0.0405
  -8.500  -0.8489   0.03647   0.02778  -0.0135   1.0000   0.0424
  -8.250  -0.8353   0.03420   0.02535  -0.0117   1.0000   0.0439
  -8.000  -0.8193   0.03261   0.02359  -0.0101   1.0000   0.0454
  -7.750  -0.8027   0.03137   0.02219  -0.0085   1.0000   0.0476
  -7.500  -0.7852   0.03003   0.02061  -0.0069   1.0000   0.0501
  -7.250  -0.7660   0.02855   0.01884  -0.0053   1.0000   0.0520
  -7.000  -0.7458   0.02727   0.01728  -0.0039   1.0000   0.0535
  -6.750  -0.7264   0.02593   0.01597  -0.0027   1.0000   0.0560
  -6.500  -0.7069   0.02500   0.01498  -0.0014   1.0000   0.0586
  -6.250  -0.6867   0.02401   0.01389  -0.0001   1.0000   0.0607
  -6.000  -0.6665   0.02307   0.01284   0.0013   1.0000   0.0628
  -5.750  -0.6468   0.02223   0.01189   0.0029   1.0000   0.0650
  -5.500  -0.6286   0.02134   0.01099   0.0045   1.0000   0.0676
  -5.250  -0.6104   0.02067   0.01033   0.0061   1.0000   0.0719
  -5.000  -0.5918   0.02006   0.00966   0.0077   1.0000   0.0769
  -4.750  -0.5740   0.01936   0.00895   0.0095   1.0000   0.0818
  -4.500  -0.5557   0.01874   0.00833   0.0112   1.0000   0.0891
  -4.250  -0.5372   0.01812   0.00774   0.0128   1.0000   0.1000
  -4.000  -0.5183   0.01754   0.00723   0.0142   1.0000   0.1187
  -3.750  -0.4992   0.01694   0.00681   0.0156   1.0000   0.1521
  -3.500  -0.4806   0.01624   0.00644   0.0169   1.0000   0.2133
  -3.250  -0.4630   0.01534   0.00608   0.0183   1.0000   0.3177
  -3.000  -0.4485   0.01413   0.00592   0.0206   1.0000   0.5178
  -2.750  -0.4300   0.01362   0.00622   0.0233   1.0000   0.6942
  -2.500  -0.4069   0.01370   0.00651   0.0253   1.0000   0.7785
  -2.250  -0.3824   0.01386   0.00669   0.0266   1.0000   0.8220
  -2.000  -0.3568   0.01410   0.00691   0.0277   1.0000   0.8599
  -1.750  -0.3256   0.01445   0.00721   0.0278   1.0000   0.8944
  -1.500  -0.2849   0.01491   0.00760   0.0259   0.9996   0.9253
  -1.250  -0.2354   0.01536   0.00795   0.0220   0.9992   0.9490
  -1.000  -0.1856   0.01556   0.00806   0.0174   0.9977   0.9603
  -0.750  -0.1373   0.01565   0.00806   0.0127   0.9950   0.9659
  -0.500  -0.0926   0.01570   0.00806   0.0087   0.9910   0.9726
  -0.250  -0.0456   0.01572   0.00805   0.0042   0.9870   0.9774
   0.000   0.0000   0.01574   0.00805   0.0000   0.9827   0.9827
   0.250   0.0456   0.01572   0.00805  -0.0042   0.9774   0.9870
   0.500   0.0926   0.01570   0.00805  -0.0087   0.9726   0.9910
   0.750   0.1374   0.01565   0.00806  -0.0127   0.9659   0.9950
   1.000   0.1857   0.01556   0.00805  -0.0174   0.9603   0.9977
   1.250   0.2354   0.01536   0.00794  -0.0220   0.9491   0.9993
   1.500   0.2849   0.01491   0.00760  -0.0259   0.9253   0.9996
   1.750   0.3256   0.01445   0.00721  -0.0278   0.8944   1.0000
   2.000   0.3568   0.01409   0.00691  -0.0277   0.8599   1.0000
   2.250   0.3824   0.01386   0.00669  -0.0266   0.8220   1.0000
   2.500   0.4069   0.01369   0.00651  -0.0253   0.7785   1.0000
   2.750   0.4299   0.01362   0.00621  -0.0233   0.6938   1.0000
   3.000   0.4484   0.01413   0.00591  -0.0205   0.5178   1.0000
   3.250   0.4630   0.01533   0.00607  -0.0183   0.3181   1.0000
   3.500   0.4805   0.01624   0.00643  -0.0169   0.2133   1.0000
   3.750   0.4992   0.01693   0.00681  -0.0156   0.1522   1.0000
   4.000   0.5182   0.01753   0.00723  -0.0142   0.1187   1.0000
   4.250   0.5371   0.01812   0.00773  -0.0128   0.1001   1.0000
   4.500   0.5556   0.01874   0.00833  -0.0111   0.0892   1.0000
   4.750   0.5739   0.01936   0.00895  -0.0095   0.0818   1.0000
   5.000   0.5917   0.02006   0.00965  -0.0077   0.0769   1.0000
   5.250   0.6104   0.02067   0.01033  -0.0061   0.0719   1.0000
   5.500   0.6286   0.02134   0.01098  -0.0045   0.0676   1.0000
   5.750   0.6468   0.02223   0.01189  -0.0029   0.0650   1.0000
   6.000   0.6665   0.02307   0.01284  -0.0013   0.0628   1.0000
   6.250   0.6866   0.02401   0.01389   0.0001   0.0607   1.0000
   6.500   0.7069   0.02500   0.01498   0.0014   0.0586   1.0000
   6.750   0.7264   0.02593   0.01597   0.0027   0.0560   1.0000
   7.000   0.7457   0.02727   0.01728   0.0039   0.0535   1.0000
   7.250   0.7659   0.02855   0.01884   0.0053   0.0520   1.0000
   7.500   0.7851   0.03003   0.02061   0.0069   0.0501   1.0000
   7.750   0.8027   0.03137   0.02219   0.0085   0.0476   1.0000
   8.000   0.8193   0.03261   0.02359   0.0101   0.0454   1.0000
   8.250   0.8353   0.03420   0.02535   0.0117   0.0439   1.0000
   8.500   0.8489   0.03647   0.02778   0.0135   0.0424   1.0000
   8.750   0.8580   0.03869   0.03057   0.0162   0.0405   1.0000
   9.000   0.8649   0.04128   0.03362   0.0188   0.0387   1.0000
   9.250   0.8691   0.04423   0.03697   0.0215   0.0375   1.0000
   9.500   0.8724   0.04693   0.03998   0.0240   0.0364   1.0000
   9.750   0.8778   0.04897   0.04220   0.0260   0.0351   1.0000
  10.000   0.8841   0.05068   0.04400   0.0278   0.0339   1.0000
  10.250   0.8832   0.05350   0.04689   0.0298   0.0331   1.0000
  10.500   0.8647   0.05743   0.05125   0.0330   0.0327   1.0000
  10.750   0.8417   0.06125   0.05534   0.0361   0.0325   1.0000
  11.000   0.8177   0.06570   0.06000   0.0371   0.0325   1.0000
  11.250   0.7929   0.07111   0.06558   0.0357   0.0326   1.0000
  11.500   0.7683   0.07791   0.07251   0.0318   0.0328   1.0000
  11.750   0.7448   0.08661   0.08129   0.0255   0.0330   1.0000
<< Back to NACA 0010-64 (naca001064-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0010-64 (naca001064-il)