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NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
Reynolds number: 50,000
Max Cl/Cd: 23.79 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls421-il-50000.txt
Download as CSV file: xf-ls421-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0421 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7343   0.09295   0.08555  -0.0541   1.0000   0.1575
 -11.250  -0.7677   0.08860   0.08114  -0.0518   1.0000   0.1566
 -11.000  -0.8056   0.08473   0.07721  -0.0485   1.0000   0.1556
 -10.750  -0.8483   0.08138   0.07379  -0.0440   1.0000   0.1544
 -10.500  -0.8879   0.07749   0.06972  -0.0403   1.0000   0.1534
 -10.250  -0.9191   0.07352   0.06551  -0.0369   1.0000   0.1529
 -10.000  -0.9405   0.06972   0.06140  -0.0340   1.0000   0.1532
  -9.750  -0.9544   0.06607   0.05740  -0.0316   1.0000   0.1541
  -9.500  -0.9622   0.06255   0.05345  -0.0296   1.0000   0.1555
  -9.250  -0.9644   0.05921   0.04957  -0.0280   1.0000   0.1572
  -9.000  -0.9505   0.05689   0.04728  -0.0269   1.0000   0.1602
  -8.750  -0.9368   0.05506   0.04541  -0.0258   1.0000   0.1642
  -8.500  -0.9256   0.05283   0.04286  -0.0248   1.0000   0.1689
  -8.250  -0.9118   0.05061   0.04035  -0.0240   1.0000   0.1737
  -8.000  -0.8941   0.04917   0.03897  -0.0230   1.0000   0.1796
  -7.750  -0.8777   0.04744   0.03685  -0.0223   1.0000   0.1872
  -7.500  -0.8590   0.04618   0.03583  -0.0211   1.0000   0.1955
  -7.250  -0.8404   0.04475   0.03425  -0.0203   1.0000   0.2060
  -7.000  -0.8217   0.04368   0.03324  -0.0192   1.0000   0.2193
  -6.750  -0.8029   0.04265   0.03241  -0.0179   1.0000   0.2354
  -6.500  -0.7843   0.04159   0.03144  -0.0168   1.0000   0.2579
  -6.250  -0.7670   0.04065   0.03095  -0.0152   1.0000   0.2861
  -6.000  -0.7501   0.03951   0.03022  -0.0139   1.0000   0.3292
  -5.750  -0.7343   0.03834   0.02977  -0.0123   1.0000   0.3955
  -5.500  -0.7235   0.03878   0.03114  -0.0073   1.0000   0.4720
  -5.250  -0.7138   0.04125   0.03401  -0.0001   1.0000   0.5271
  -5.000  -0.7015   0.04420   0.03698   0.0064   1.0000   0.5657
  -4.750  -0.6879   0.04675   0.03943   0.0117   1.0000   0.5995
  -4.500  -0.6742   0.04961   0.04222   0.0179   1.0000   0.6220
  -4.250  -0.6597   0.05210   0.04461   0.0236   1.0000   0.6442
  -4.000  -0.6445   0.05420   0.04662   0.0288   1.0000   0.6664
  -3.750  -0.6285   0.05595   0.04826   0.0334   1.0000   0.6890
  -3.500  -0.6116   0.05737   0.04956   0.0375   1.0000   0.7120
  -3.250  -0.5940   0.05843   0.05051   0.0410   1.0000   0.7356
  -3.000  -0.5765   0.05914   0.05111   0.0440   1.0000   0.7598
  -2.750  -0.5635   0.05935   0.05121   0.0468   1.0000   0.7850
  -2.500  -0.5398   0.05981   0.05155   0.0484   1.0000   0.8083
  -2.250  -0.5010   0.06055   0.05214   0.0474   1.0000   0.8317
  -2.000  -0.4650   0.06092   0.05237   0.0458   1.0000   0.8559
  -1.750  -0.4396   0.06086   0.05218   0.0451   1.0000   0.8787
  -1.500  -0.3761   0.06161   0.05277   0.0374   1.0000   0.8980
  -1.250  -0.3361   0.06177   0.05281   0.0332   1.0000   0.9149
  -1.000  -0.3012   0.06187   0.05280   0.0297   1.0000   0.9300
  -0.750  -0.2666   0.06206   0.05289   0.0259   1.0000   0.9437
  -0.500  -0.2320   0.06237   0.05311   0.0219   1.0000   0.9562
  -0.250  -0.1967   0.06283   0.05349   0.0177   1.0000   0.9679
   0.000  -0.1599   0.06349   0.05407   0.0130   1.0000   0.9786
   0.250  -0.1171   0.06435   0.05488   0.0069   1.0000   0.9881
   0.500  -0.0791   0.06532   0.05581   0.0017   1.0000   0.9968
   0.750  -0.0632   0.06581   0.05627   0.0006   1.0000   1.0000
   1.000  -0.0608   0.06588   0.05632   0.0023   1.0000   1.0000
   1.250  -0.0585   0.06599   0.05642   0.0039   1.0000   1.0000
   1.500  -0.0563   0.06614   0.05657   0.0055   1.0000   1.0000
   1.750  -0.0542   0.06632   0.05675   0.0072   1.0000   1.0000
   2.000  -0.0522   0.06654   0.05696   0.0088   1.0000   1.0000
   2.250  -0.0503   0.06679   0.05721   0.0104   1.0000   1.0000
   2.500  -0.0326   0.06765   0.05809   0.0087   0.9946   1.0000
   2.750   0.0102   0.07005   0.06049   0.0023   0.9776   1.0000
   3.000   0.0378   0.07107   0.06154  -0.0009   0.9576   1.0000
   3.250   0.0640   0.07236   0.06285  -0.0037   0.9371   1.0000
   3.500   0.0852   0.07358   0.06409  -0.0054   0.9184   1.0000
   3.750   0.1046   0.07475   0.06528  -0.0066   0.8991   1.0000
   4.000   0.1220   0.07593   0.06649  -0.0074   0.8810   1.0000
   4.250   0.1403   0.07708   0.06765  -0.0081   0.8608   1.0000
   4.500   0.1580   0.07805   0.06865  -0.0086   0.8386   1.0000
   4.750   0.2784   0.07629   0.06680  -0.0175   0.7430   1.0000
   5.000   0.3047   0.07626   0.06677  -0.0174   0.7216   1.0000
   5.250   0.3192   0.07620   0.06673  -0.0161   0.7020   1.0000
   5.500   0.3298   0.07618   0.06674  -0.0143   0.6834   1.0000
   5.750   0.3402   0.07617   0.06675  -0.0125   0.6652   1.0000
   6.000   0.3511   0.07616   0.06676  -0.0107   0.6475   1.0000
   6.250   0.3636   0.07611   0.06674  -0.0091   0.6301   1.0000
   6.500   0.3792   0.07605   0.06671  -0.0078   0.6130   1.0000
   6.750   0.4008   0.07594   0.06663  -0.0072   0.5957   1.0000
   7.000   0.4279   0.07575   0.06649  -0.0072   0.5787   1.0000
   7.250   0.4627   0.07519   0.06598  -0.0078   0.5621   1.0000
   7.500   0.5123   0.07352   0.06437  -0.0089   0.5471   1.0000
   7.750   0.5363   0.07346   0.06438  -0.0088   0.5289   1.0000
   8.000   0.5619   0.07336   0.06435  -0.0089   0.5107   1.0000
   8.250   0.5876   0.07333   0.06439  -0.0089   0.4926   1.0000
   8.500   0.6145   0.07323   0.06436  -0.0090   0.4747   1.0000
   8.750   0.7173   0.06448   0.05569  -0.0097   0.4693   1.0000
   9.000   0.7477   0.06349   0.05477  -0.0094   0.4516   1.0000
   9.250   0.7880   0.06152   0.05284  -0.0093   0.4347   1.0000
   9.500   0.8908   0.05328   0.04454  -0.0107   0.4193   1.0000
   9.750   1.0389   0.04464   0.03533  -0.0171   0.3897   1.0000
  10.000   1.0684   0.04554   0.03614  -0.0178   0.3688   1.0000
  10.250   1.1039   0.04640   0.03685  -0.0191   0.3494   1.0000
  10.500   1.1007   0.04906   0.03970  -0.0174   0.3365   1.0000
  10.750   1.1198   0.05096   0.04162  -0.0177   0.3229   1.0000
  11.000   1.1631   0.05188   0.04240  -0.0198   0.3084   1.0000
  11.250   1.1518   0.05522   0.04600  -0.0179   0.3001   1.0000
  11.500   1.1857   0.05671   0.04740  -0.0193   0.2889   1.0000
  11.750   1.1546   0.06145   0.05251  -0.0165   0.2840   1.0000
  12.000   1.2162   0.06158   0.05241  -0.0197   0.2721   1.0000
  12.250   1.1610   0.06801   0.05930  -0.0160   0.2702   1.0000
  12.500   1.0616   0.08009   0.07183  -0.0134   0.2710   1.0000
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