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NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
Reynolds number: 50,000
Max Cl/Cd: 35.8 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413mod-il-50000-n5.txt
Download as CSV file: xf-ls413mod-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5277   0.07972   0.07204  -0.0562   1.0000   0.0591
 -10.000  -0.5413   0.07569   0.06802  -0.0570   1.0000   0.0588
  -9.750  -0.5573   0.07190   0.06422  -0.0574   1.0000   0.0585
  -9.500  -0.5712   0.06815   0.06041  -0.0574   1.0000   0.0583
  -9.250  -0.5825   0.06456   0.05671  -0.0568   1.0000   0.0580
  -9.000  -0.5905   0.06107   0.05304  -0.0561   1.0000   0.0578
  -8.750  -0.5948   0.05769   0.04944  -0.0552   1.0000   0.0578
  -8.500  -0.5955   0.05443   0.04588  -0.0543   1.0000   0.0580
  -8.250  -0.5925   0.05130   0.04240  -0.0534   1.0000   0.0585
  -8.000  -0.5856   0.04836   0.03902  -0.0526   1.0000   0.0591
  -7.750  -0.5743   0.04583   0.03630  -0.0518   1.0000   0.0600
  -7.500  -0.5608   0.04367   0.03398  -0.0511   1.0000   0.0609
  -7.250  -0.5454   0.04161   0.03171  -0.0503   1.0000   0.0617
  -7.000  -0.5284   0.03960   0.02944  -0.0496   1.0000   0.0624
  -6.750  -0.5101   0.03776   0.02736  -0.0489   1.0000   0.0633
  -6.500  -0.4908   0.03611   0.02548  -0.0482   1.0000   0.0643
  -6.250  -0.4707   0.03465   0.02380  -0.0474   1.0000   0.0657
  -6.000  -0.4503   0.03340   0.02234  -0.0465   1.0000   0.0680
  -5.750  -0.4293   0.03234   0.02102  -0.0456   1.0000   0.0707
  -5.500  -0.4097   0.03133   0.02010  -0.0447   1.0000   0.0737
  -5.250  -0.3892   0.03052   0.01925  -0.0436   1.0000   0.0769
  -5.000  -0.3549   0.02963   0.01817  -0.0448   0.9949   0.0815
  -4.750  -0.3212   0.02873   0.01732  -0.0464   0.9894   0.0892
  -4.500  -0.2857   0.02784   0.01641  -0.0484   0.9840   0.1006
  -4.250  -0.2506   0.02682   0.01547  -0.0507   0.9780   0.1208
  -4.000  -0.2133   0.02529   0.01446  -0.0541   0.9726   0.1842
  -3.750  -0.1820   0.02332   0.01460  -0.0560   0.9685   0.4968
  -3.500  -0.1630   0.02402   0.01563  -0.0522   0.9594   0.6375
  -3.250  -0.1393   0.02483   0.01634  -0.0498   0.9510   0.7028
  -3.000  -0.1202   0.02568   0.01710  -0.0460   0.9425   0.7495
  -2.750  -0.1028   0.02621   0.01752  -0.0422   0.9334   0.7823
  -2.500  -0.0787   0.02651   0.01767  -0.0401   0.9259   0.8085
  -2.250  -0.0570   0.02662   0.01762  -0.0384   0.9167   0.8301
  -2.000  -0.0272   0.02659   0.01743  -0.0381   0.9097   0.8480
  -1.750  -0.0035   0.02653   0.01723  -0.0372   0.9003   0.8633
  -1.500   0.0318   0.02641   0.01695  -0.0387   0.8935   0.8760
  -1.250   0.0572   0.02629   0.01671  -0.0384   0.8838   0.8873
  -1.000   0.0937   0.02611   0.01640  -0.0400   0.8770   0.8981
  -0.750   0.1196   0.02602   0.01622  -0.0400   0.8668   0.9091
  -0.500   0.1571   0.02583   0.01592  -0.0418   0.8601   0.9186
  -0.250   0.1840   0.02574   0.01578  -0.0420   0.8492   0.9281
   0.000   0.2243   0.02553   0.01549  -0.0443   0.8428   0.9362
   0.250   0.2512   0.02552   0.01544  -0.0447   0.8314   0.9458
   0.500   0.2896   0.02539   0.01527  -0.0469   0.8233   0.9531
   1.000   0.3597   0.02532   0.01519  -0.0503   0.8031   0.9685
   1.250   0.4022   0.02514   0.01500  -0.0530   0.7946   0.9752
   1.500   0.4365   0.02516   0.01505  -0.0546   0.7820   0.9837
   1.750   0.4747   0.02506   0.01498  -0.0567   0.7699   0.9921
   2.000   0.5082   0.02480   0.01473  -0.0575   0.7582   1.0000
   2.250   0.5356   0.02467   0.01462  -0.0573   0.7451   1.0000
   2.500   0.5604   0.02466   0.01464  -0.0568   0.7302   1.0000
   2.750   0.5877   0.02460   0.01461  -0.0567   0.7151   1.0000
   3.000   0.6163   0.02452   0.01457  -0.0567   0.6996   1.0000
   3.250   0.6457   0.02443   0.01453  -0.0567   0.6834   1.0000
   3.500   0.6755   0.02433   0.01446  -0.0568   0.6664   1.0000
   3.750   0.7061   0.02417   0.01434  -0.0569   0.6478   1.0000
   4.000   0.7335   0.02413   0.01433  -0.0566   0.6255   1.0000
   4.250   0.7617   0.02406   0.01428  -0.0563   0.6015   1.0000
   4.500   0.7892   0.02408   0.01432  -0.0560   0.5754   1.0000
   4.750   0.8176   0.02410   0.01429  -0.0558   0.5485   1.0000
   5.000   0.8436   0.02431   0.01448  -0.0554   0.5183   1.0000
   5.250   0.8692   0.02460   0.01469  -0.0550   0.4862   1.0000
   5.500   0.8938   0.02502   0.01502  -0.0544   0.4528   1.0000
   5.750   0.9166   0.02560   0.01545  -0.0538   0.4182   1.0000
   6.000   0.9382   0.02634   0.01605  -0.0532   0.3841   1.0000
   6.250   0.9587   0.02720   0.01680  -0.0525   0.3521   1.0000
   6.500   0.9784   0.02817   0.01761  -0.0518   0.3234   1.0000
   6.750   0.9982   0.02921   0.01856  -0.0512   0.2983   1.0000
   7.000   1.0179   0.03032   0.01954  -0.0506   0.2774   1.0000
   7.250   1.0380   0.03146   0.02059  -0.0500   0.2595   1.0000
   7.500   1.0591   0.03260   0.02170  -0.0496   0.2439   1.0000
   7.750   1.0808   0.03376   0.02287  -0.0493   0.2298   1.0000
   8.000   1.1028   0.03494   0.02412  -0.0490   0.2176   1.0000
   8.250   1.1257   0.03614   0.02533  -0.0488   0.2076   1.0000
   8.500   1.1484   0.03736   0.02658  -0.0486   0.1983   1.0000
   8.750   1.1702   0.03868   0.02803  -0.0483   0.1895   1.0000
   9.000   1.1930   0.03995   0.02931  -0.0482   0.1820   1.0000
   9.250   1.2151   0.04147   0.03104  -0.0479   0.1753   1.0000
   9.500   1.2365   0.04291   0.03259  -0.0476   0.1690   1.0000
   9.750   1.2569   0.04449   0.03427  -0.0472   0.1631   1.0000
  10.000   1.2723   0.04624   0.03630  -0.0463   0.1571   1.0000
  10.250   1.2941   0.04778   0.03785  -0.0461   0.1521   1.0000
  10.500   1.3056   0.04990   0.04027  -0.0450   0.1473   1.0000
  10.750   1.3117   0.05188   0.04251  -0.0432   0.1422   1.0000
  11.000   1.3299   0.05320   0.04375  -0.0426   0.1367   1.0000
  11.250   1.3237   0.05585   0.04681  -0.0401   0.1326   1.0000
  11.500   1.3206   0.05833   0.04956  -0.0383   0.1280   1.0000
  11.750   1.3317   0.05983   0.05103  -0.0373   0.1231   1.0000
  12.000   1.3242   0.06298   0.05447  -0.0358   0.1197   1.0000
  12.250   1.3081   0.06699   0.05886  -0.0346   0.1168   1.0000
  12.500   1.2961   0.07087   0.06300  -0.0340   0.1137   1.0000
  12.750   1.2991   0.07326   0.06544  -0.0336   0.1100   1.0000
  13.000   1.2932   0.07686   0.06916  -0.0335   0.1072   1.0000
  13.250   1.2596   0.08395   0.07663  -0.0350   0.1062   1.0000
  13.500   1.2184   0.09303   0.08603  -0.0385   0.1057   1.0000
  13.750   1.1610   0.10632   0.09960  -0.0456   0.1062   1.0000
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