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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 50,000
Max Cl/Cd: 37.42 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2408-il-50000.txt
Download as CSV file: xf-naca2408-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5158   0.11581   0.10876  -0.0005   1.0000   0.2147
  -9.000  -0.5047   0.11139   0.10435   0.0000   1.0000   0.2243
  -8.750  -0.5244   0.11068   0.10379  -0.0033   1.0000   0.2309
  -8.500  -0.5127   0.10634   0.09946  -0.0023   1.0000   0.2449
  -8.250  -0.5012   0.10208   0.09521  -0.0015   1.0000   0.2582
  -8.000  -0.4921   0.09805   0.09121  -0.0010   1.0000   0.2692
  -7.750  -0.4902   0.09472   0.08794  -0.0011   1.0000   0.2807
  -7.250  -0.4846   0.08830   0.08163  -0.0003   1.0000   0.3105
  -7.000  -0.4846   0.08558   0.07899   0.0007   1.0000   0.3308
  -6.750  -0.4857   0.08261   0.07611   0.0014   1.0000   0.3510
  -6.500  -0.4754   0.07928   0.07280   0.0035   1.0000   0.3751
  -6.250  -0.4705   0.07597   0.06952   0.0049   1.0000   0.3970
  -5.500  -0.4465   0.04776   0.04000  -0.0398   1.0000   0.1601
  -5.250  -0.4272   0.04311   0.03498  -0.0403   1.0000   0.1525
  -5.000  -0.4072   0.03925   0.03059  -0.0407   1.0000   0.1547
  -4.750  -0.3850   0.03567   0.02638  -0.0408   1.0000   0.1562
  -4.500  -0.3609   0.03247   0.02253  -0.0405   1.0000   0.1573
  -4.250  -0.3387   0.03039   0.02033  -0.0397   1.0000   0.1676
  -4.000  -0.3137   0.02816   0.01765  -0.0392   1.0000   0.1754
  -3.750  -0.2883   0.02626   0.01548  -0.0385   1.0000   0.1834
  -3.500  -0.2627   0.02455   0.01358  -0.0378   1.0000   0.1952
  -3.250  -0.2371   0.02316   0.01202  -0.0371   1.0000   0.2177
  -3.000  -0.2125   0.02182   0.01085  -0.0362   1.0000   0.2541
  -2.750  -0.1858   0.02018   0.00951  -0.0355   1.0000   0.3257
  -2.500  -0.1645   0.01790   0.00857  -0.0337   1.0000   0.5168
  -2.250  -0.1218   0.01600   0.00775  -0.0327   1.0000   1.0000
  -2.000  -0.1006   0.01601   0.00727  -0.0320   1.0000   1.0000
  -1.750  -0.0793   0.01607   0.00695  -0.0313   1.0000   1.0000
  -1.500  -0.0579   0.01616   0.00673  -0.0306   1.0000   1.0000
  -1.250  -0.0363   0.01628   0.00657  -0.0300   1.0000   1.0000
  -1.000  -0.0147   0.01644   0.00651  -0.0294   1.0000   1.0000
  -0.750   0.0068   0.01664   0.00651  -0.0288   1.0000   1.0000
  -0.500   0.0283   0.01687   0.00656  -0.0284   1.0000   1.0000
  -0.250   0.0497   0.01714   0.00669  -0.0279   1.0000   1.0000
   0.000   0.0709   0.01747   0.00690  -0.0276   1.0000   1.0000
   0.250   0.0918   0.01784   0.00717  -0.0273   1.0000   1.0000
   0.500   0.1125   0.01826   0.00751  -0.0271   1.0000   1.0000
   0.750   0.1327   0.01875   0.00795  -0.0269   1.0000   1.0000
   1.000   0.1525   0.01931   0.00846  -0.0268   1.0000   1.0000
   1.250   0.1719   0.01995   0.00907  -0.0269   1.0000   1.0000
   1.500   0.1907   0.02066   0.00978  -0.0270   1.0000   1.0000
   1.750   0.2090   0.02146   0.01058  -0.0272   1.0000   1.0000
   2.000   0.2269   0.02235   0.01148  -0.0275   1.0000   1.0000
   2.250   0.2794   0.02355   0.01277  -0.0342   0.9858   1.0000
   2.500   0.3384   0.02464   0.01398  -0.0418   0.9647   1.0000
   2.750   0.3896   0.02553   0.01504  -0.0475   0.9419   1.0000
   3.000   0.4445   0.02628   0.01599  -0.0533   0.9200   1.0000
   3.250   0.4931   0.02685   0.01679  -0.0576   0.8964   1.0000
   3.500   0.5394   0.02726   0.01745  -0.0609   0.8722   1.0000
   3.750   0.5930   0.02730   0.01783  -0.0647   0.8485   1.0000
   4.000   0.6410   0.02703   0.01789  -0.0665   0.8235   1.0000
   4.250   0.6805   0.02667   0.01786  -0.0664   0.7957   1.0000
   4.500   0.7211   0.02559   0.01708  -0.0647   0.7638   1.0000
   4.750   0.7519   0.02392   0.01557  -0.0597   0.7179   1.0000
   5.000   0.7757   0.02239   0.01406  -0.0536   0.6627   1.0000
   5.250   0.7942   0.02177   0.01339  -0.0486   0.6037   1.0000
   5.500   0.8098   0.02164   0.01319  -0.0440   0.5323   1.0000
   5.750   0.8138   0.02235   0.01317  -0.0376   0.3749   1.0000
   6.000   0.8187   0.02581   0.01499  -0.0334   0.2201   1.0000
   6.250   0.8401   0.02806   0.01686  -0.0320   0.1788   1.0000
   6.500   0.8678   0.03023   0.01896  -0.0312   0.1592   1.0000
   6.750   0.8978   0.03268   0.02152  -0.0306   0.1477   1.0000
   7.000   0.9250   0.03533   0.02433  -0.0300   0.1382   1.0000
   7.250   0.9498   0.03812   0.02711  -0.0294   0.1278   1.0000
   7.500   0.9712   0.04130   0.03099  -0.0279   0.1244   1.0000
   7.750   0.9897   0.04448   0.03461  -0.0265   0.1187   1.0000
   8.000   1.0078   0.04832   0.03866  -0.0255   0.1136   1.0000
   8.250   1.0203   0.05265   0.04355  -0.0238   0.1134   1.0000
   8.500   1.0281   0.05723   0.04867  -0.0221   0.1135   1.0000
   8.750   1.0307   0.06193   0.05388  -0.0205   0.1134   1.0000
   9.000   1.0303   0.06688   0.05923  -0.0191   0.1136   1.0000
   9.250   1.0245   0.07189   0.06468  -0.0179   0.1155   1.0000
   9.500   0.9834   0.07910   0.07244  -0.0181   0.1245   1.0000
   9.750   0.9758   0.08468   0.07811  -0.0182   0.1267   1.0000
  10.000   0.7879   0.08467   0.07838  -0.0136   0.1366   1.0000
  10.250   0.7659   0.09338   0.08709  -0.0175   0.1439   1.0000
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