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NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)
Reynolds number: 50,000
Max Cl/Cd: 25.87 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls013-il-50000-n5.txt
Download as CSV file: xf-ls013-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0013 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7957   0.09361   0.08615  -0.0140   1.0000   0.0718
 -11.750  -0.8295   0.08470   0.07712  -0.0194   1.0000   0.0713
 -11.500  -0.8606   0.07768   0.06992  -0.0226   1.0000   0.0709
 -11.250  -0.8874   0.07209   0.06411  -0.0238   1.0000   0.0708
 -11.000  -0.9098   0.06750   0.05927  -0.0234   1.0000   0.0709
 -10.750  -0.9268   0.06349   0.05496  -0.0220   1.0000   0.0713
 -10.500  -0.9370   0.05956   0.05064  -0.0207   1.0000   0.0721
 -10.250  -0.9429   0.05583   0.04641  -0.0192   1.0000   0.0734
 -10.000  -0.9358   0.05284   0.04318  -0.0183   1.0000   0.0752
  -9.750  -0.9214   0.05060   0.04084  -0.0178   1.0000   0.0775
  -9.500  -0.9078   0.04813   0.03813  -0.0171   1.0000   0.0798
  -9.250  -0.8929   0.04553   0.03517  -0.0164   1.0000   0.0822
  -9.000  -0.8774   0.04310   0.03226  -0.0156   1.0000   0.0856
  -8.750  -0.8566   0.04105   0.03011  -0.0154   1.0000   0.0890
  -8.500  -0.8342   0.03928   0.02825  -0.0152   1.0000   0.0926
  -8.250  -0.8115   0.03755   0.02623  -0.0149   1.0000   0.0973
  -8.000  -0.7869   0.03589   0.02445  -0.0147   1.0000   0.1023
  -7.750  -0.7615   0.03449   0.02303  -0.0147   1.0000   0.1074
  -7.500  -0.7355   0.03321   0.02149  -0.0144   1.0000   0.1144
  -7.250  -0.7102   0.03198   0.02039  -0.0143   1.0000   0.1214
  -7.000  -0.6837   0.03088   0.01916  -0.0140   1.0000   0.1298
  -6.750  -0.6612   0.02982   0.01818  -0.0135   1.0000   0.1398
  -6.500  -0.6406   0.02878   0.01718  -0.0127   1.0000   0.1515
  -6.250  -0.6227   0.02776   0.01623  -0.0115   1.0000   0.1654
  -6.000  -0.6085   0.02676   0.01538  -0.0100   1.0000   0.1841
  -5.750  -0.5979   0.02579   0.01460  -0.0078   1.0000   0.2087
  -5.500  -0.5913   0.02478   0.01389  -0.0051   1.0000   0.2440
  -5.250  -0.5860   0.02373   0.01322  -0.0022   1.0000   0.2979
  -5.000  -0.5807   0.02267   0.01269   0.0009   1.0000   0.3769
  -4.750  -0.5722   0.02212   0.01293   0.0048   1.0000   0.4812
  -4.500  -0.5582   0.02251   0.01371   0.0089   1.0000   0.5758
  -4.250  -0.5453   0.02286   0.01405   0.0122   1.0000   0.6325
  -4.000  -0.5321   0.02323   0.01432   0.0154   1.0000   0.6737
  -3.750  -0.5068   0.02384   0.01480   0.0169   0.9949   0.7109
  -3.500  -0.4787   0.02456   0.01539   0.0182   0.9890   0.7420
  -3.250  -0.4493   0.02530   0.01599   0.0194   0.9837   0.7706
  -3.000  -0.4194   0.02587   0.01642   0.0203   0.9787   0.7954
  -2.750  -0.3896   0.02615   0.01655   0.0204   0.9733   0.8152
  -2.500  -0.3535   0.02632   0.01656   0.0192   0.9692   0.8292
  -2.250  -0.3186   0.02641   0.01651   0.0180   0.9646   0.8409
  -2.000  -0.2850   0.02640   0.01637   0.0166   0.9596   0.8522
  -1.750  -0.2499   0.02636   0.01621   0.0148   0.9552   0.8640
  -1.500  -0.2117   0.02641   0.01617   0.0126   0.9510   0.8744
  -1.250  -0.1752   0.02642   0.01609   0.0107   0.9462   0.8849
  -1.000  -0.1399   0.02637   0.01598   0.0086   0.9417   0.8954
  -0.750  -0.0997   0.02634   0.01589   0.0056   0.9374   0.9013
  -0.500  -0.0723   0.02628   0.01579   0.0048   0.9309   0.9093
  -0.250  -0.0311   0.02625   0.01574   0.0015   0.9266   0.9142
   0.000   0.0000   0.02625   0.01573   0.0000   0.9204   0.9204
   0.250   0.0311   0.02625   0.01574  -0.0015   0.9142   0.9266
   0.500   0.0723   0.02628   0.01579  -0.0048   0.9093   0.9309
   0.750   0.0997   0.02634   0.01589  -0.0056   0.9013   0.9374
   1.000   0.1399   0.02637   0.01598  -0.0086   0.8954   0.9417
   1.250   0.1752   0.02641   0.01609  -0.0107   0.8850   0.9463
   1.500   0.2117   0.02641   0.01616  -0.0126   0.8744   0.9510
   1.750   0.2499   0.02636   0.01621  -0.0148   0.8640   0.9552
   2.000   0.2850   0.02639   0.01636  -0.0166   0.8522   0.9596
   2.250   0.3186   0.02640   0.01651  -0.0180   0.8409   0.9646
   2.500   0.3535   0.02632   0.01656  -0.0192   0.8292   0.9692
   2.750   0.3896   0.02615   0.01655  -0.0204   0.8152   0.9733
   3.000   0.4194   0.02587   0.01642  -0.0203   0.7954   0.9787
   3.250   0.4493   0.02530   0.01598  -0.0194   0.7706   0.9837
   3.500   0.4787   0.02456   0.01538  -0.0182   0.7420   0.9890
   3.750   0.5068   0.02384   0.01479  -0.0169   0.7109   0.9949
   4.000   0.5320   0.02323   0.01431  -0.0154   0.6737   1.0000
   4.250   0.5452   0.02286   0.01404  -0.0122   0.6327   1.0000
   4.500   0.5581   0.02250   0.01370  -0.0088   0.5760   1.0000
   4.750   0.5720   0.02211   0.01293  -0.0048   0.4814   1.0000
   5.000   0.5806   0.02266   0.01268  -0.0009   0.3771   1.0000
   5.250   0.5859   0.02372   0.01321   0.0022   0.2981   1.0000
   5.500   0.5912   0.02478   0.01389   0.0051   0.2441   1.0000
   5.750   0.5978   0.02578   0.01459   0.0078   0.2087   1.0000
   6.000   0.6085   0.02676   0.01537   0.0100   0.1841   1.0000
   6.250   0.6228   0.02776   0.01623   0.0115   0.1654   1.0000
   6.500   0.6407   0.02878   0.01718   0.0127   0.1515   1.0000
   6.750   0.6613   0.02982   0.01818   0.0135   0.1398   1.0000
   7.000   0.6838   0.03088   0.01916   0.0140   0.1298   1.0000
   7.250   0.7103   0.03198   0.02039   0.0143   0.1214   1.0000
   7.500   0.7356   0.03321   0.02149   0.0144   0.1144   1.0000
   7.750   0.7617   0.03449   0.02303   0.0146   0.1074   1.0000
   8.000   0.7870   0.03590   0.02445   0.0147   0.1023   1.0000
   8.250   0.8116   0.03755   0.02623   0.0149   0.0973   1.0000
   8.500   0.8344   0.03929   0.02825   0.0152   0.0926   1.0000
   8.750   0.8568   0.04105   0.03012   0.0154   0.0890   1.0000
   9.000   0.8776   0.04310   0.03226   0.0156   0.0856   1.0000
   9.250   0.8931   0.04553   0.03517   0.0164   0.0822   1.0000
   9.500   0.9080   0.04813   0.03813   0.0171   0.0798   1.0000
   9.750   0.9216   0.05061   0.04085   0.0178   0.0775   1.0000
  10.000   0.9361   0.05285   0.04318   0.0183   0.0752   1.0000
  10.250   0.9431   0.05585   0.04643   0.0191   0.0734   1.0000
  10.500   0.9372   0.05958   0.05066   0.0206   0.0721   1.0000
  10.750   0.9271   0.06351   0.05499   0.0220   0.0713   1.0000
  11.000   0.9101   0.06753   0.05930   0.0233   0.0709   1.0000
  11.250   0.8878   0.07213   0.06416   0.0237   0.0708   1.0000
  11.500   0.8610   0.07775   0.06999   0.0224   0.0709   1.0000
  11.750   0.8299   0.08479   0.07721   0.0192   0.0713   1.0000
  12.000   0.7962   0.09372   0.08626   0.0138   0.0718   1.0000
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