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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 50,000
Max Cl/Cd: 33.79 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413-il-50000-n5.txt
Download as CSV file: xf-ls413-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4484   0.10255   0.09480  -0.0499   1.0000   0.0657
 -10.500  -0.4580   0.09715   0.08948  -0.0522   1.0000   0.0643
 -10.000  -0.5493   0.08005   0.07244  -0.0616   1.0000   0.0598
  -9.750  -0.5707   0.07735   0.06981  -0.0597   1.0000   0.0596
  -9.500  -0.5901   0.07437   0.06684  -0.0582   1.0000   0.0593
  -9.250  -0.6075   0.07138   0.06380  -0.0564   1.0000   0.0590
  -9.000  -0.6221   0.06827   0.06059  -0.0548   1.0000   0.0588
  -8.750  -0.6327   0.06507   0.05723  -0.0533   1.0000   0.0586
  -8.500  -0.6389   0.06177   0.05371  -0.0521   1.0000   0.0584
  -8.250  -0.6405   0.05845   0.05012  -0.0512   1.0000   0.0582
  -8.000  -0.6376   0.05519   0.04653  -0.0506   1.0000   0.0583
  -7.750  -0.6304   0.05204   0.04298  -0.0502   1.0000   0.0588
  -7.500  -0.6191   0.04909   0.03955  -0.0500   1.0000   0.0596
  -7.250  -0.6044   0.04642   0.03652  -0.0499   1.0000   0.0605
  -7.000  -0.5876   0.04422   0.03416  -0.0496   1.0000   0.0615
  -6.750  -0.5690   0.04221   0.03191  -0.0493   1.0000   0.0624
  -6.500  -0.5488   0.04027   0.02971  -0.0490   1.0000   0.0632
  -6.250  -0.5274   0.03854   0.02772  -0.0487   1.0000   0.0642
  -6.000  -0.5017   0.03692   0.02585  -0.0490   0.9989   0.0655
  -5.750  -0.4706   0.03549   0.02414  -0.0501   0.9960   0.0681
  -5.500  -0.4386   0.03433   0.02265  -0.0510   0.9932   0.0715
  -5.250  -0.4105   0.03318   0.02157  -0.0514   0.9901   0.0748
  -5.000  -0.3816   0.03230   0.02061  -0.0517   0.9870   0.0783
  -4.750  -0.3518   0.03162   0.01972  -0.0520   0.9843   0.0837
  -4.500  -0.3226   0.03080   0.01899  -0.0528   0.9816   0.0908
  -4.250  -0.2941   0.03006   0.01817  -0.0534   0.9780   0.0991
  -4.000  -0.2628   0.02924   0.01740  -0.0550   0.9746   0.1140
  -3.750  -0.2288   0.02817   0.01656  -0.0574   0.9717   0.1450
  -3.250  -0.1788   0.02621   0.01727  -0.0567   0.9655   0.6070
  -3.000  -0.1578   0.02710   0.01809  -0.0541   0.9601   0.6862
  -2.750  -0.1486   0.02839   0.01943  -0.0472   0.9551   0.7507
  -2.500  -0.1448   0.02900   0.02001  -0.0403   0.9489   0.7911
  -2.250  -0.1268   0.02921   0.02008  -0.0374   0.9441   0.8151
  -2.000  -0.0980   0.02929   0.01995  -0.0376   0.9405   0.8300
  -1.750  -0.0787   0.02928   0.01979  -0.0362   0.9348   0.8444
  -1.500  -0.0534   0.02929   0.01965  -0.0360   0.9298   0.8583
  -1.250  -0.0235   0.02931   0.01952  -0.0366   0.9257   0.8699
  -1.000  -0.0013   0.02928   0.01938  -0.0360   0.9199   0.8805
  -0.750   0.0249   0.02929   0.01929  -0.0362   0.9143   0.8914
  -0.500   0.0574   0.02936   0.01925  -0.0377   0.9100   0.9015
  -0.250   0.0813   0.02938   0.01920  -0.0376   0.9040   0.9106
   0.000   0.1096   0.02946   0.01923  -0.0385   0.8980   0.9192
   0.250   0.1447   0.02957   0.01927  -0.0405   0.8934   0.9268
   0.500   0.1692   0.02971   0.01937  -0.0407   0.8864   0.9348
   0.750   0.2009   0.02986   0.01950  -0.0423   0.8803   0.9428
   1.000   0.2387   0.03001   0.01964  -0.0448   0.8752   0.9500
   1.250   0.2648   0.03019   0.01984  -0.0454   0.8659   0.9589
   1.500   0.3081   0.03030   0.01996  -0.0488   0.8601   0.9662
   1.750   0.3358   0.03050   0.02021  -0.0497   0.8494   0.9765
   2.000   0.3741   0.03060   0.02035  -0.0522   0.8416   0.9892
   2.250   0.4026   0.03075   0.02056  -0.0531   0.8311   1.0000
   2.500   0.4334   0.03099   0.02086  -0.0544   0.8208   1.0000
   2.750   0.4779   0.03085   0.02079  -0.0572   0.8120   1.0000
   3.000   0.5083   0.03088   0.02091  -0.0580   0.7982   1.0000
   3.250   0.5412   0.03080   0.02092  -0.0589   0.7844   1.0000
   3.500   0.5771   0.03044   0.02067  -0.0599   0.7695   1.0000
   3.750   0.6149   0.02974   0.02009  -0.0606   0.7525   1.0000
   4.000   0.6520   0.02896   0.01943  -0.0611   0.7348   1.0000
   4.250   0.6882   0.02823   0.01884  -0.0614   0.7165   1.0000
   4.500   0.7137   0.02787   0.01862  -0.0605   0.6930   1.0000
   4.750   0.7458   0.02711   0.01798  -0.0600   0.6674   1.0000
   5.000   0.7679   0.02688   0.01787  -0.0586   0.6332   1.0000
   5.250   0.7927   0.02658   0.01765  -0.0574   0.5896   1.0000
   5.500   0.8316   0.02563   0.01652  -0.0572   0.5250   1.0000
   5.750   0.8646   0.02559   0.01591  -0.0566   0.4367   1.0000
   6.000   0.8810   0.02665   0.01644  -0.0549   0.3677   1.0000
   6.250   0.8940   0.02797   0.01738  -0.0532   0.3170   1.0000
   6.500   0.9082   0.02937   0.01845  -0.0519   0.2806   1.0000
   6.750   0.9254   0.03068   0.01961  -0.0510   0.2511   1.0000
   7.000   0.9444   0.03194   0.02073  -0.0504   0.2289   1.0000
   7.250   0.9654   0.03315   0.02186  -0.0500   0.2102   1.0000
   7.500   0.9881   0.03433   0.02299  -0.0498   0.1949   1.0000
   7.750   1.0136   0.03548   0.02409  -0.0498   0.1822   1.0000
   8.000   1.0406   0.03663   0.02519  -0.0501   0.1704   1.0000
   8.250   1.0702   0.03781   0.02649  -0.0507   0.1596   1.0000
   8.500   1.1004   0.03912   0.02783  -0.0514   0.1506   1.0000
   8.750   1.1277   0.04047   0.02926  -0.0518   0.1421   1.0000
   9.000   1.1570   0.04204   0.03096  -0.0524   0.1348   1.0000
   9.250   1.1804   0.04356   0.03262  -0.0524   0.1280   1.0000
   9.500   1.2048   0.04526   0.03438  -0.0525   0.1223   1.0000
   9.750   1.2243   0.04715   0.03657  -0.0519   0.1168   1.0000
  10.000   1.2443   0.04879   0.03824  -0.0516   0.1120   1.0000
  10.250   1.2605   0.05096   0.04068  -0.0507   0.1078   1.0000
  10.500   1.2705   0.05331   0.04339  -0.0492   0.1039   1.0000
  10.750   1.2808   0.05535   0.04561  -0.0477   0.1004   1.0000
  11.000   1.2985   0.05722   0.04743  -0.0473   0.0970   1.0000
  11.250   1.2941   0.06022   0.05087  -0.0445   0.0947   1.0000
  11.500   1.2873   0.06350   0.05458  -0.0420   0.0927   1.0000
  11.750   1.2790   0.06686   0.05828  -0.0397   0.0908   1.0000
  12.000   1.2698   0.07029   0.06198  -0.0379   0.0890   1.0000
  12.250   1.2609   0.07373   0.06565  -0.0365   0.0874   1.0000
  12.500   1.2568   0.07687   0.06892  -0.0355   0.0857   1.0000
  12.750   1.2623   0.07957   0.07161  -0.0350   0.0839   1.0000
  13.000   1.2318   0.08537   0.07778  -0.0346   0.0835   1.0000
  13.250   1.1981   0.09222   0.08493  -0.0356   0.0834   1.0000
  13.500   1.1600   0.10054   0.09352  -0.0385   0.0834   1.0000
  13.750   1.1166   0.11115   0.10436  -0.0440   0.0837   1.0000
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