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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 50,000
Max Cl/Cd: 35.91 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls413-il-50000.txt
Download as CSV file: xf-ls413-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3907   0.11981   0.11232  -0.0277   1.0000   0.3031
 -10.000  -0.3723   0.11561   0.10814  -0.0269   1.0000   0.3127
  -9.500  -0.3980   0.11304   0.10580  -0.0250   1.0000   0.3374
  -9.250  -0.3762   0.10902   0.10178  -0.0236   1.0000   0.3518
  -9.000  -0.3625   0.10546   0.09824  -0.0224   1.0000   0.3621
  -8.500  -0.3805   0.10210   0.09510  -0.0183   1.0000   0.3879
  -8.250  -0.3646   0.09866   0.09167  -0.0170   1.0000   0.3969
  -8.000  -0.3711   0.09663   0.08974  -0.0146   1.0000   0.4075
  -7.000  -0.6057   0.06059   0.05311  -0.0441   1.0000   0.1599
  -6.750  -0.5916   0.05682   0.04921  -0.0441   1.0000   0.1545
  -6.500  -0.5733   0.05116   0.04244  -0.0480   1.0000   0.1426
  -6.250  -0.5535   0.04772   0.03885  -0.0483   1.0000   0.1406
  -6.000  -0.5307   0.04446   0.03524  -0.0492   1.0000   0.1378
  -5.750  -0.5050   0.04149   0.03181  -0.0501   1.0000   0.1353
  -5.500  -0.4776   0.03896   0.02883  -0.0509   1.0000   0.1342
  -5.250  -0.4506   0.03698   0.02650  -0.0513   1.0000   0.1359
  -5.000  -0.4235   0.03537   0.02452  -0.0515   1.0000   0.1398
  -4.750  -0.3965   0.03390   0.02272  -0.0514   1.0000   0.1437
  -4.500  -0.3725   0.03247   0.02135  -0.0506   1.0000   0.1486
  -4.250  -0.3482   0.03151   0.02026  -0.0497   1.0000   0.1571
  -4.000  -0.3259   0.03051   0.01939  -0.0484   1.0000   0.1689
  -3.750  -0.3029   0.02958   0.01856  -0.0471   1.0000   0.1846
  -3.500  -0.2771   0.02842   0.01768  -0.0470   1.0000   0.2183
  -3.000  -0.2729   0.02819   0.02047  -0.0295   1.0000   0.7487
  -2.750  -0.2795   0.02896   0.02114  -0.0196   1.0000   0.7969
  -2.500  -0.2836   0.02918   0.02126  -0.0109   1.0000   0.8381
  -2.250  -0.1270   0.03035   0.02167  -0.0231   1.0000   1.0000
  -2.000  -0.1273   0.02995   0.02116  -0.0205   1.0000   1.0000
  -1.750  -0.1270   0.02957   0.02068  -0.0179   1.0000   1.0000
  -1.500  -0.1262   0.02920   0.02023  -0.0153   1.0000   1.0000
  -1.250  -0.1248   0.02886   0.01979  -0.0128   1.0000   1.0000
  -1.000  -0.1225   0.02853   0.01938  -0.0103   1.0000   1.0000
  -0.750  -0.1190   0.02824   0.01902  -0.0081   1.0000   1.0000
  -0.500  -0.1111   0.02807   0.01876  -0.0067   1.0000   1.0000
  -0.250  -0.0971   0.02808   0.01868  -0.0063   1.0000   1.0000
   0.000  -0.0783   0.02827   0.01876  -0.0068   1.0000   1.0000
   0.250  -0.0560   0.02861   0.01901  -0.0079   1.0000   1.0000
   0.500  -0.0316   0.02907   0.01939  -0.0095   1.0000   1.0000
   0.750  -0.0059   0.02964   0.01988  -0.0113   1.0000   1.0000
   1.000   0.0206   0.03030   0.02048  -0.0132   1.0000   1.0000
   1.250   0.0474   0.03104   0.02118  -0.0153   1.0000   1.0000
   1.500   0.0743   0.03187   0.02197  -0.0174   1.0000   1.0000
   1.750   0.1011   0.03277   0.02286  -0.0195   1.0000   1.0000
   2.000   0.1276   0.03376   0.02384  -0.0217   1.0000   1.0000
   2.250   0.1536   0.03482   0.02492  -0.0238   1.0000   1.0000
   2.500   0.1790   0.03597   0.02609  -0.0260   1.0000   1.0000
   2.750   0.2077   0.03730   0.02746  -0.0288   0.9975   1.0000
   3.000   0.2869   0.03974   0.02995  -0.0402   0.9655   1.0000
   3.500   0.3932   0.04258   0.03297  -0.0523   0.9146   1.0000
   3.750   0.4466   0.04361   0.03413  -0.0575   0.8878   1.0000
   4.000   0.5069   0.04404   0.03470  -0.0627   0.8577   1.0000
   4.250   0.5698   0.04372   0.03457  -0.0671   0.8277   1.0000
   4.500   0.6137   0.04329   0.03431  -0.0686   0.7981   1.0000
   4.750   0.6634   0.04221   0.03346  -0.0699   0.7685   1.0000
   5.000   0.7189   0.04006   0.03155  -0.0706   0.7382   1.0000
   5.250   0.7766   0.03679   0.02859  -0.0702   0.7076   1.0000
   5.500   0.8372   0.03238   0.02448  -0.0688   0.6721   1.0000
   5.750   0.8869   0.02822   0.02050  -0.0657   0.6090   1.0000
   6.000   0.9343   0.02602   0.01723  -0.0625   0.4703   1.0000
   6.250   0.9576   0.02782   0.01811  -0.0610   0.3871   1.0000
   6.500   0.9881   0.02966   0.01948  -0.0614   0.3371   1.0000
   6.750   1.0212   0.03142   0.02095  -0.0623   0.3032   1.0000
   7.000   1.0578   0.03333   0.02263  -0.0638   0.2783   1.0000
   7.250   1.0879   0.03522   0.02455  -0.0644   0.2589   1.0000
   7.500   1.1186   0.03727   0.02663  -0.0652   0.2439   1.0000
   7.750   1.1475   0.03936   0.02872  -0.0657   0.2304   1.0000
   8.000   1.1727   0.04154   0.03111  -0.0657   0.2195   1.0000
   8.250   1.1936   0.04405   0.03392  -0.0651   0.2103   1.0000
   8.500   1.2230   0.04661   0.03634  -0.0659   0.2008   1.0000
   8.750   1.2314   0.04949   0.03989  -0.0636   0.1952   1.0000
   9.000   1.2531   0.05205   0.04255  -0.0633   0.1875   1.0000
   9.250   1.2619   0.05553   0.04641  -0.0616   0.1829   1.0000
   9.500   1.2605   0.05928   0.05070  -0.0588   0.1799   1.0000
   9.750   1.2585   0.06303   0.05485  -0.0562   0.1767   1.0000
  10.000   1.2912   0.06620   0.05778  -0.0575   0.1697   1.0000
  10.250   1.2759   0.07055   0.06264  -0.0539   0.1690   1.0000
  10.500   1.2572   0.07526   0.06775  -0.0507   0.1688   1.0000
  10.750   1.2352   0.08020   0.07299  -0.0477   0.1690   1.0000
  11.000   1.2107   0.08517   0.07818  -0.0449   0.1694   1.0000
  11.250   0.9681   0.11754   0.11095  -0.0596   0.2035   1.0000
  11.500   0.9819   0.12121   0.11467  -0.0589   0.2013   1.0000
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