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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 100,000
Max Cl/Cd: 48.85 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413-il-100000-n5.txt
Download as CSV file: xf-ls413-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4670   0.09408   0.08855  -0.0534   1.0000   0.0397
 -10.750  -0.4786   0.08779   0.08232  -0.0563   1.0000   0.0391
 -10.500  -0.5070   0.07802   0.07259  -0.0620   1.0000   0.0381
 -10.250  -0.5542   0.07020   0.06474  -0.0649   1.0000   0.0372
 -10.000  -0.6012   0.06659   0.06111  -0.0620   1.0000   0.0368
  -9.750  -0.6423   0.06369   0.05814  -0.0583   1.0000   0.0364
  -9.500  -0.6631   0.05862   0.05275  -0.0590   0.9969   0.0361
  -9.250  -0.6534   0.05399   0.04777  -0.0626   0.9912   0.0363
  -9.000  -0.6372   0.05047   0.04396  -0.0653   0.9859   0.0368
  -8.750  -0.6172   0.04697   0.04011  -0.0682   0.9818   0.0375
  -8.500  -0.5990   0.04377   0.03653  -0.0697   0.9764   0.0380
  -8.250  -0.5753   0.04057   0.03289  -0.0718   0.9725   0.0383
  -8.000  -0.5473   0.03762   0.02949  -0.0741   0.9697   0.0385
  -7.750  -0.5239   0.03533   0.02684  -0.0747   0.9646   0.0388
  -7.500  -0.4957   0.03323   0.02440  -0.0760   0.9608   0.0393
  -7.250  -0.4647   0.03136   0.02220  -0.0774   0.9580   0.0399
  -7.000  -0.4319   0.02971   0.02027  -0.0790   0.9559   0.0407
  -6.750  -0.4057   0.02850   0.01881  -0.0791   0.9513   0.0416
  -6.500  -0.3776   0.02729   0.01758  -0.0798   0.9474   0.0432
  -6.250  -0.3466   0.02633   0.01660  -0.0810   0.9445   0.0452
  -6.000  -0.3141   0.02537   0.01557  -0.0823   0.9422   0.0472
  -5.750  -0.2806   0.02443   0.01454  -0.0837   0.9405   0.0491
  -5.500  -0.2583   0.02369   0.01379  -0.0830   0.9348   0.0509
  -5.250  -0.2286   0.02292   0.01308  -0.0841   0.9312   0.0542
  -5.000  -0.1955   0.02230   0.01239  -0.0856   0.9284   0.0593
  -4.750  -0.1610   0.02154   0.01166  -0.0875   0.9263   0.0651
  -4.500  -0.1262   0.02091   0.01104  -0.0894   0.9244   0.0750
  -4.250  -0.1033   0.02049   0.01067  -0.0891   0.9186   0.0887
  -4.000  -0.0718   0.01963   0.01018  -0.0907   0.9154   0.1442
  -3.750  -0.0355   0.01790   0.00974  -0.0945   0.9135   0.4026
  -3.500  -0.0087   0.01775   0.01036  -0.0936   0.9108   0.5716
  -3.250   0.0232   0.01805   0.01068  -0.0937   0.9085   0.6391
  -3.000   0.0384   0.01875   0.01142  -0.0904   0.9014   0.6844
  -2.750   0.0593   0.01940   0.01208  -0.0875   0.8970   0.7167
  -2.500   0.0880   0.01964   0.01224  -0.0870   0.8940   0.7327
  -2.250   0.1149   0.01975   0.01226  -0.0867   0.8898   0.7409
  -2.000   0.1392   0.01989   0.01232  -0.0862   0.8843   0.7485
  -1.750   0.1669   0.02000   0.01237  -0.0860   0.8807   0.7574
  -1.500   0.1974   0.02004   0.01235  -0.0863   0.8779   0.7658
  -1.250   0.2246   0.02012   0.01238  -0.0862   0.8738   0.7725
  -1.000   0.2498   0.02026   0.01248  -0.0860   0.8677   0.7794
  -0.750   0.2774   0.02028   0.01247  -0.0857   0.8637   0.7850
  -0.500   0.3114   0.02023   0.01238  -0.0870   0.8610   0.7919
  -0.250   0.3341   0.02040   0.01255  -0.0862   0.8548   0.7972
   0.000   0.3604   0.02046   0.01262  -0.0860   0.8497   0.8020
   0.250   0.3938   0.02040   0.01254  -0.0872   0.8463   0.8071
   0.500   0.4283   0.02030   0.01244  -0.0885   0.8434   0.8112
   0.750   0.4478   0.02046   0.01264  -0.0870   0.8343   0.8151
   1.000   0.4825   0.02018   0.01236  -0.0879   0.8295   0.8190
   1.250   0.5097   0.02013   0.01235  -0.0879   0.8202   0.8234
   1.500   0.5441   0.01982   0.01205  -0.0887   0.8138   0.8271
   1.750   0.5691   0.01965   0.01193  -0.0877   0.8031   0.8307
   2.000   0.6021   0.01913   0.01143  -0.0878   0.7922   0.8344
   2.250   0.6350   0.01863   0.01094  -0.0880   0.7794   0.8385
   2.500   0.6621   0.01843   0.01078  -0.0875   0.7652   0.8427
   2.750   0.6871   0.01822   0.01065  -0.0865   0.7509   0.8464
   3.000   0.7142   0.01798   0.01044  -0.0859   0.7340   0.8505
   3.250   0.7429   0.01774   0.01023  -0.0856   0.7149   0.8551
   3.500   0.7664   0.01767   0.01024  -0.0845   0.6914   0.8594
   3.750   0.7917   0.01750   0.01008  -0.0835   0.6644   0.8634
   4.000   0.8171   0.01741   0.00997  -0.0827   0.6264   0.8680
   4.250   0.8449   0.01735   0.00968  -0.0820   0.5625   0.8728
   4.500   0.8641   0.01769   0.00955  -0.0798   0.4804   0.8774
   4.750   0.8789   0.01851   0.00988  -0.0775   0.4009   0.8829
   5.000   0.8945   0.01941   0.01042  -0.0757   0.3351   0.8883
   5.250   0.9086   0.02021   0.01094  -0.0735   0.2865   0.8938
   5.500   0.9256   0.02099   0.01152  -0.0720   0.2486   0.9002
   5.750   0.9420   0.02167   0.01206  -0.0703   0.2193   0.9070
   6.000   0.9593   0.02233   0.01264  -0.0688   0.1973   0.9149
   6.250   0.9759   0.02296   0.01321  -0.0671   0.1808   0.9233
   6.500   0.9928   0.02363   0.01383  -0.0656   0.1674   0.9330
   6.750   1.0096   0.02427   0.01446  -0.0641   0.1563   0.9452
   7.000   1.0272   0.02486   0.01511  -0.0627   0.1468   0.9655
   7.250   1.0445   0.02565   0.01585  -0.0616   0.1389   1.0000
   7.500   1.0675   0.02645   0.01673  -0.0615   0.1305   1.0000
   7.750   1.0876   0.02745   0.01765  -0.0611   0.1240   1.0000
   8.000   1.1102   0.02831   0.01863  -0.0608   0.1175   1.0000
   8.250   1.1300   0.02930   0.01960  -0.0603   0.1119   1.0000
   8.500   1.1511   0.03030   0.02066  -0.0599   0.1067   1.0000
   8.750   1.1716   0.03129   0.02171  -0.0595   0.1017   1.0000
   9.000   1.1900   0.03241   0.02280  -0.0588   0.0975   1.0000
   9.250   1.2106   0.03349   0.02402  -0.0583   0.0931   1.0000
   9.500   1.2297   0.03459   0.02521  -0.0576   0.0890   1.0000
   9.750   1.2466   0.03575   0.02637  -0.0568   0.0855   1.0000
  10.000   1.2646   0.03704   0.02776  -0.0560   0.0821   1.0000
  10.250   1.2821   0.03830   0.02920  -0.0551   0.0785   1.0000
  10.500   1.2972   0.03956   0.03055  -0.0541   0.0754   1.0000
  10.750   1.3112   0.04090   0.03189  -0.0531   0.0729   1.0000
  11.000   1.3258   0.04246   0.03364  -0.0520   0.0703   1.0000
  11.250   1.3388   0.04406   0.03547  -0.0508   0.0676   1.0000
  11.500   1.3498   0.04564   0.03719  -0.0496   0.0652   1.0000
  11.750   1.3594   0.04719   0.03881  -0.0483   0.0632   1.0000
  12.000   1.3700   0.04887   0.04049  -0.0472   0.0616   1.0000
  12.250   1.3766   0.05110   0.04304  -0.0457   0.0599   1.0000
  12.500   1.3808   0.05347   0.04570  -0.0442   0.0581   1.0000
  12.750   1.3833   0.05588   0.04835  -0.0428   0.0566   1.0000
  13.000   1.3848   0.05827   0.05092  -0.0416   0.0552   1.0000
  13.250   1.3862   0.06063   0.05341  -0.0405   0.0540   1.0000
  13.500   1.3885   0.06295   0.05580  -0.0396   0.0529   1.0000
  13.750   1.3917   0.06539   0.05828  -0.0388   0.0520   1.0000
  14.000   1.3799   0.06948   0.06272  -0.0379   0.0512   1.0000
  14.250   1.3655   0.07408   0.06767  -0.0376   0.0505   1.0000
  14.500   1.3478   0.07923   0.07315  -0.0378   0.0500   1.0000
  14.750   1.3267   0.08512   0.07934  -0.0388   0.0495   1.0000
  15.000   1.3012   0.09206   0.08658  -0.0410   0.0492   1.0000
  15.250   1.2698   0.10074   0.09556  -0.0450   0.0491   1.0000
  15.500   1.2242   0.11344   0.10859  -0.0526   0.0493   1.0000
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