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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 100,000
Max Cl/Cd: 53.04 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls413-il-100000.txt
Download as CSV file: xf-ls413-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4516   0.09762   0.09264  -0.0421   1.0000   0.1572
  -9.250  -0.3810   0.09551   0.09101  -0.0312   1.0000   0.1637
  -9.000  -0.4534   0.09266   0.08780  -0.0373   1.0000   0.1645
  -8.750  -0.4675   0.09091   0.08614  -0.0347   1.0000   0.1693
  -8.500  -0.5127   0.08902   0.08440  -0.0323   1.0000   0.1723
  -8.250  -0.5731   0.08555   0.08107  -0.0329   1.0000   0.1735
  -8.000  -0.5858   0.08176   0.07733  -0.0317   1.0000   0.1770
  -7.750  -0.5597   0.08184   0.07745  -0.0253   1.0000   0.1836
  -7.500  -0.6229   0.07492   0.07040  -0.0329   1.0000   0.1920
  -7.250  -0.5944   0.07442   0.07009  -0.0264   1.0000   0.1970
  -6.500  -0.5794   0.04394   0.03687  -0.0475   1.0000   0.0957
  -6.250  -0.5494   0.03988   0.03184  -0.0488   1.0000   0.0837
  -6.000  -0.5246   0.03655   0.02836  -0.0496   1.0000   0.0817
  -5.750  -0.4983   0.03419   0.02569  -0.0501   1.0000   0.0801
  -5.500  -0.4715   0.03227   0.02345  -0.0505   1.0000   0.0792
  -5.250  -0.4450   0.03073   0.02164  -0.0507   1.0000   0.0793
  -5.000  -0.4191   0.02964   0.02032  -0.0507   1.0000   0.0813
  -4.750  -0.3932   0.02881   0.01923  -0.0506   1.0000   0.0833
  -4.500  -0.3672   0.02751   0.01789  -0.0506   1.0000   0.0852
  -4.250  -0.3415   0.02651   0.01699  -0.0506   1.0000   0.0881
  -4.000  -0.3156   0.02585   0.01635  -0.0506   1.0000   0.0925
  -3.750  -0.2886   0.02522   0.01574  -0.0509   1.0000   0.0997
  -3.500  -0.2549   0.02465   0.01528  -0.0526   0.9986   0.1112
  -3.250  -0.2120   0.02387   0.01475  -0.0564   0.9962   0.1393
  -3.000  -0.1679   0.02234   0.01598  -0.0592   0.9953   0.6795
  -2.750  -0.1498   0.02352   0.01715  -0.0555   0.9904   0.7233
  -2.500  -0.1308   0.02448   0.01806  -0.0524   0.9855   0.7532
  -2.250  -0.1118   0.02535   0.01888  -0.0493   0.9810   0.7811
  -2.000  -0.1076   0.02602   0.01957  -0.0427   0.9754   0.8126
  -1.750  -0.1033   0.02653   0.02009  -0.0356   0.9705   0.8467
  -1.500  -0.0991   0.02657   0.02011  -0.0298   0.9649   0.8747
  -1.250  -0.0810   0.02653   0.01999  -0.0276   0.9596   0.8921
  -1.000  -0.0441   0.02680   0.02013  -0.0300   0.9553   0.9031
  -0.750  -0.0300   0.02662   0.01990  -0.0278   0.9487   0.9159
  -0.500  -0.0043   0.02661   0.01981  -0.0278   0.9434   0.9290
  -0.250   0.0246   0.02670   0.01983  -0.0286   0.9380   0.9393
   0.000   0.0511   0.02669   0.01977  -0.0292   0.9302   0.9495
   0.250   0.0956   0.02695   0.01995  -0.0328   0.9247   0.9597
   0.500   0.1197   0.02693   0.01991  -0.0332   0.9149   0.9695
   0.750   0.1714   0.02723   0.02016  -0.0383   0.9089   0.9766
   1.000   0.2013   0.02740   0.02033  -0.0399   0.8985   0.9848
   1.500   0.2775   0.02786   0.02079  -0.0457   0.8809   1.0000
   1.750   0.3165   0.02804   0.02098  -0.0484   0.8710   1.0000
   2.000   0.3653   0.02799   0.02094  -0.0524   0.8615   1.0000
   2.250   0.3980   0.02807   0.02105  -0.0539   0.8490   1.0000
   2.500   0.4404   0.02793   0.02096  -0.0566   0.8377   1.0000
   2.750   0.5068   0.02680   0.01987  -0.0617   0.8281   1.0000
   3.000   0.5452   0.02625   0.01939  -0.0631   0.8139   1.0000
   3.250   0.5848   0.02568   0.01890  -0.0646   0.8010   1.0000
   3.500   0.6562   0.02355   0.01687  -0.0694   0.7950   1.0000
   3.750   0.6949   0.02251   0.01592  -0.0701   0.7806   1.0000
   4.000   0.7341   0.02141   0.01493  -0.0707   0.7660   1.0000
   4.250   0.7740   0.02024   0.01386  -0.0714   0.7501   1.0000
   4.500   0.8152   0.01897   0.01268  -0.0721   0.7315   1.0000
   4.750   0.8432   0.01830   0.01212  -0.0712   0.7037   1.0000
   5.000   0.8753   0.01747   0.01132  -0.0708   0.6654   1.0000
   5.250   0.9016   0.01700   0.01075  -0.0694   0.5924   1.0000
   5.500   0.9224   0.01753   0.01026  -0.0671   0.4442   1.0000
   5.750   0.9317   0.01927   0.01113  -0.0645   0.3392   1.0000
   6.000   0.9473   0.02085   0.01215  -0.0632   0.2828   1.0000
   6.250   0.9688   0.02224   0.01319  -0.0629   0.2483   1.0000
   6.500   0.9937   0.02340   0.01420  -0.0631   0.2234   1.0000
   6.750   1.0206   0.02460   0.01523  -0.0636   0.2055   1.0000
   7.000   1.0489   0.02580   0.01634  -0.0643   0.1907   1.0000
   7.250   1.0786   0.02706   0.01755  -0.0652   0.1785   1.0000
   7.500   1.1101   0.02848   0.01882  -0.0664   0.1680   1.0000
   7.750   1.1382   0.02966   0.02007  -0.0670   0.1583   1.0000
   8.000   1.1691   0.03122   0.02166  -0.0680   0.1501   1.0000
   8.250   1.1968   0.03252   0.02298  -0.0686   0.1422   1.0000
   8.500   1.2258   0.03430   0.02487  -0.0693   0.1355   1.0000
   8.750   1.2502   0.03567   0.02639  -0.0692   0.1290   1.0000
   9.000   1.2788   0.03771   0.02839  -0.0701   0.1232   1.0000
   9.250   1.2982   0.03936   0.03041  -0.0691   0.1181   1.0000
   9.500   1.3211   0.04090   0.03201  -0.0689   0.1131   1.0000
   9.750   1.3427   0.04347   0.03473  -0.0688   0.1089   1.0000
  10.000   1.3542   0.04567   0.03738  -0.0667   0.1053   1.0000
  10.250   1.3705   0.04762   0.03952  -0.0656   0.1015   1.0000
  10.500   1.3914   0.04973   0.04161  -0.0655   0.0980   1.0000
  10.750   1.3984   0.05330   0.04553  -0.0636   0.0959   1.0000
  11.000   1.3934   0.05634   0.04908  -0.0599   0.0944   1.0000
  11.250   1.3849   0.05965   0.05284  -0.0561   0.0930   1.0000
  11.500   1.3714   0.06296   0.05650  -0.0520   0.0918   1.0000
  11.750   1.3528   0.06637   0.06022  -0.0478   0.0910   1.0000
  12.000   1.3304   0.07023   0.06439  -0.0442   0.0905   1.0000
  12.250   1.3021   0.07489   0.06934  -0.0412   0.0904   1.0000
  12.500   1.2663   0.08065   0.07541  -0.0394   0.0909   1.0000
  12.750   1.2236   0.08789   0.08292  -0.0393   0.0918   1.0000
  13.000   1.1773   0.09681   0.09206  -0.0415   0.0932   1.0000
  13.250   1.1337   0.10717   0.10258  -0.0459   0.0947   1.0000
  13.500   1.0995   0.11802   0.11353  -0.0514   0.0959   1.0000
  13.750   1.0805   0.12761   0.12315  -0.0558   0.0967   1.0000
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