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NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-65 (naca001065-il)
Reynolds number: 50,000
Max Cl/Cd: 21.84 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001065-il-50000-n5.txt
Download as CSV file: xf-naca001065-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-65                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6383   0.09900   0.09137  -0.0332   1.0000   0.0652
 -10.500  -0.6533   0.09227   0.08469  -0.0372   1.0000   0.0644
 -10.250  -0.6738   0.08626   0.07869  -0.0395   1.0000   0.0636
 -10.000  -0.6984   0.08124   0.07365  -0.0394   1.0000   0.0628
  -9.750  -0.7250   0.07723   0.06960  -0.0369   1.0000   0.0622
  -9.500  -0.7490   0.07365   0.06594  -0.0332   1.0000   0.0619
  -9.250  -0.7670   0.07010   0.06226  -0.0297   1.0000   0.0619
  -9.000  -0.7814   0.06662   0.05860  -0.0259   1.0000   0.0620
  -8.750  -0.7926   0.06316   0.05491  -0.0220   1.0000   0.0622
  -8.500  -0.8005   0.05981   0.05130  -0.0182   1.0000   0.0625
  -8.250  -0.8046   0.05671   0.04791  -0.0144   1.0000   0.0635
  -8.000  -0.8060   0.05387   0.04475  -0.0107   1.0000   0.0654
  -7.750  -0.8062   0.05095   0.04141  -0.0068   1.0000   0.0675
  -7.500  -0.8039   0.04798   0.03792  -0.0030   1.0000   0.0691
  -7.250  -0.7973   0.04511   0.03450   0.0004   1.0000   0.0702
  -7.000  -0.7864   0.04241   0.03138   0.0031   1.0000   0.0713
  -6.750  -0.7716   0.04046   0.02930   0.0049   1.0000   0.0740
  -6.500  -0.7560   0.03884   0.02749   0.0068   1.0000   0.0778
  -6.250  -0.7383   0.03690   0.02515   0.0087   1.0000   0.0808
  -6.000  -0.7170   0.03493   0.02275   0.0101   1.0000   0.0829
  -5.750  -0.6931   0.03317   0.02064   0.0111   1.0000   0.0853
  -5.500  -0.6686   0.03165   0.01905   0.0116   1.0000   0.0885
  -5.250  -0.6447   0.03054   0.01781   0.0123   1.0000   0.0946
  -5.000  -0.6173   0.02939   0.01651   0.0125   1.0000   0.1012
  -4.750  -0.5887   0.02833   0.01540   0.0126   1.0000   0.1077
  -4.500  -0.5601   0.02735   0.01426   0.0126   1.0000   0.1159
  -4.250  -0.5361   0.02648   0.01330   0.0134   1.0000   0.1277
  -4.000  -0.5157   0.02560   0.01255   0.0146   1.0000   0.1466
  -3.750  -0.4968   0.02468   0.01179   0.0161   1.0000   0.1764
  -3.500  -0.4803   0.02355   0.01101   0.0178   1.0000   0.2321
  -3.000  -0.3297   0.02394   0.01379   0.0062   1.0000   0.9222
  -2.750  -0.1333   0.02445   0.01341  -0.0262   1.0000   1.0000
  -2.500  -0.1208   0.02420   0.01304  -0.0241   1.0000   1.0000
  -2.250  -0.1084   0.02399   0.01272  -0.0218   1.0000   1.0000
  -2.000  -0.0961   0.02380   0.01245  -0.0195   1.0000   1.0000
  -1.750  -0.0839   0.02364   0.01221  -0.0172   1.0000   1.0000
  -1.500  -0.0718   0.02351   0.01201  -0.0148   1.0000   1.0000
  -1.250  -0.0597   0.02339   0.01184  -0.0124   1.0000   1.0000
  -1.000  -0.0477   0.02330   0.01170  -0.0100   1.0000   1.0000
  -0.750  -0.0357   0.02323   0.01160  -0.0075   1.0000   1.0000
  -0.500  -0.0238   0.02318   0.01152  -0.0050   1.0000   1.0000
  -0.250  -0.0119   0.02315   0.01148  -0.0025   1.0000   1.0000
   0.000   0.0000   0.02314   0.01146   0.0000   1.0000   1.0000
   0.250   0.0119   0.02315   0.01148   0.0025   1.0000   1.0000
   0.500   0.0238   0.02318   0.01152   0.0050   1.0000   1.0000
   0.750   0.0357   0.02323   0.01159   0.0075   1.0000   1.0000
   1.000   0.0477   0.02330   0.01170   0.0100   1.0000   1.0000
   1.250   0.0597   0.02339   0.01183   0.0124   1.0000   1.0000
   1.500   0.0718   0.02350   0.01200   0.0148   1.0000   1.0000
   1.750   0.0839   0.02364   0.01220   0.0172   1.0000   1.0000
   2.000   0.0961   0.02380   0.01244   0.0195   1.0000   1.0000
   2.250   0.1085   0.02398   0.01271   0.0218   1.0000   1.0000
   2.500   0.1209   0.02419   0.01304   0.0241   1.0000   1.0000
   2.750   0.1333   0.02444   0.01339   0.0262   1.0000   1.0000
   3.000   0.3278   0.02396   0.01380  -0.0059   0.9229   1.0000
   3.250   0.4740   0.02170   0.01027  -0.0213   0.3843   1.0000
   3.500   0.4803   0.02355   0.01101  -0.0178   0.2322   1.0000
   3.750   0.4968   0.02467   0.01178  -0.0161   0.1765   1.0000
   4.000   0.5157   0.02560   0.01255  -0.0146   0.1467   1.0000
   4.250   0.5361   0.02648   0.01330  -0.0134   0.1277   1.0000
   4.500   0.5600   0.02734   0.01426  -0.0126   0.1159   1.0000
   4.750   0.5886   0.02833   0.01539  -0.0125   0.1077   1.0000
   5.000   0.6172   0.02938   0.01650  -0.0125   0.1013   1.0000
   5.250   0.6446   0.03054   0.01780  -0.0123   0.0946   1.0000
   5.500   0.6684   0.03164   0.01905  -0.0115   0.0885   1.0000
   5.750   0.6930   0.03316   0.02063  -0.0110   0.0853   1.0000
   6.000   0.7169   0.03492   0.02274  -0.0101   0.0829   1.0000
   6.250   0.7382   0.03689   0.02514  -0.0086   0.0808   1.0000
   6.500   0.7559   0.03883   0.02748  -0.0068   0.0778   1.0000
   6.750   0.7715   0.04045   0.02929  -0.0049   0.0740   1.0000
   7.000   0.7863   0.04240   0.03137  -0.0031   0.0713   1.0000
   7.250   0.7972   0.04510   0.03449  -0.0004   0.0702   1.0000
   7.500   0.8038   0.04798   0.03791   0.0030   0.0691   1.0000
   7.750   0.8062   0.05095   0.04140   0.0068   0.0675   1.0000
   8.000   0.8060   0.05386   0.04474   0.0107   0.0654   1.0000
   8.250   0.8046   0.05670   0.04790   0.0144   0.0635   1.0000
   8.500   0.8005   0.05980   0.05129   0.0182   0.0625   1.0000
   8.750   0.7927   0.06315   0.05491   0.0220   0.0622   1.0000
   9.000   0.7814   0.06661   0.05859   0.0259   0.0620   1.0000
   9.250   0.7671   0.07010   0.06226   0.0296   0.0619   1.0000
   9.500   0.7492   0.07365   0.06594   0.0332   0.0619   1.0000
   9.750   0.7253   0.07723   0.06960   0.0369   0.0622   1.0000
  10.000   0.6988   0.08125   0.07366   0.0394   0.0628   1.0000
  10.250   0.6742   0.08628   0.07871   0.0394   0.0636   1.0000
  10.500   0.6538   0.09231   0.08472   0.0371   0.0644   1.0000
  10.750   0.6389   0.09904   0.09141   0.0331   0.0651   1.0000
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