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NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
Reynolds number: 200,000
Max Cl/Cd: 66.01 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls413mod-il-200000.txt
Download as CSV file: xf-ls413mod-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4473   0.08850   0.08481  -0.0413   1.0000   0.0764
  -9.750  -0.4547   0.08335   0.07971  -0.0448   1.0000   0.0787
  -9.500  -0.5003   0.07383   0.07025  -0.0540   1.0000   0.0808
  -9.250  -0.5487   0.06982   0.06621  -0.0542   1.0000   0.0815
  -9.000  -0.6059   0.06820   0.06424  -0.0514   1.0000   0.0825
  -8.750  -0.6266   0.06326   0.05915  -0.0498   1.0000   0.0834
  -8.500  -0.5546   0.05270   0.04935  -0.0463   0.9971   0.0854
  -8.250  -0.5332   0.04882   0.04544  -0.0490   0.9938   0.0874
  -8.000  -0.5190   0.04418   0.04063  -0.0529   0.9884   0.0908
  -7.750  -0.5079   0.03720   0.03314  -0.0592   0.9831   0.0987
  -7.500  -0.5421   0.03334   0.02683  -0.0585   0.9896   0.0501
  -7.250  -0.5067   0.03061   0.02392  -0.0609   0.9864   0.0486
  -7.000  -0.4694   0.02789   0.02090  -0.0638   0.9838   0.0481
  -6.750  -0.4325   0.02608   0.01879  -0.0661   0.9802   0.0485
  -6.500  -0.3967   0.02446   0.01694  -0.0680   0.9759   0.0487
  -6.250  -0.3585   0.02291   0.01519  -0.0702   0.9727   0.0489
  -6.000  -0.3184   0.02165   0.01379  -0.0727   0.9703   0.0493
  -5.750  -0.2853   0.02031   0.01239  -0.0739   0.9654   0.0501
  -5.500  -0.2497   0.01906   0.01122  -0.0757   0.9611   0.0518
  -5.250  -0.2097   0.01818   0.01038  -0.0784   0.9581   0.0544
  -5.000  -0.1670   0.01749   0.00966  -0.0815   0.9559   0.0586
  -4.750  -0.1325   0.01652   0.00878  -0.0834   0.9498   0.0636
  -4.500  -0.0915   0.01571   0.00799  -0.0864   0.9458   0.0723
  -4.250  -0.0464   0.01416   0.00695  -0.0910   0.9431   0.1518
  -4.000   0.0015   0.01194   0.00650  -0.0972   0.9415   0.5340
  -3.750   0.0320   0.01196   0.00678  -0.0971   0.9339   0.6270
  -3.500   0.0654   0.01210   0.00693  -0.0974   0.9279   0.6697
  -3.250   0.0977   0.01225   0.00703  -0.0976   0.9215   0.6969
  -3.000   0.1232   0.01251   0.00730  -0.0961   0.9128   0.7169
  -2.750   0.1479   0.01284   0.00763  -0.0941   0.9055   0.7357
  -2.500   0.1697   0.01316   0.00795  -0.0916   0.8962   0.7519
  -2.250   0.1934   0.01342   0.00818  -0.0897   0.8882   0.7661
  -2.000   0.2159   0.01364   0.00837  -0.0876   0.8794   0.7782
  -1.750   0.2382   0.01377   0.00847  -0.0856   0.8712   0.7860
  -1.500   0.2663   0.01380   0.00844  -0.0853   0.8629   0.7957
  -1.250   0.2871   0.01390   0.00852  -0.0830   0.8545   0.8027
  -1.000   0.3152   0.01392   0.00847  -0.0827   0.8460   0.8121
  -0.750   0.3393   0.01389   0.00842  -0.0815   0.8372   0.8167
  -0.500   0.3656   0.01383   0.00831  -0.0808   0.8285   0.8218
  -0.250   0.3963   0.01379   0.00822  -0.0814   0.8180   0.8286
   0.000   0.4194   0.01368   0.00806  -0.0797   0.8082   0.8335
   0.250   0.4444   0.01361   0.00795  -0.0786   0.7960   0.8396
   0.500   0.4738   0.01355   0.00785  -0.0789   0.7838   0.8458
   0.750   0.4977   0.01345   0.00772  -0.0776   0.7731   0.8502
   1.000   0.5250   0.01338   0.00761  -0.0772   0.7622   0.8553
   1.250   0.5557   0.01336   0.00756  -0.0778   0.7494   0.8607
   1.500   0.5789   0.01323   0.00741  -0.0764   0.7354   0.8649
   1.750   0.6050   0.01314   0.00728  -0.0757   0.7199   0.8698
   2.000   0.6352   0.01311   0.00720  -0.0762   0.7044   0.8749
   2.250   0.6607   0.01302   0.00709  -0.0755   0.6898   0.8786
   2.500   0.6867   0.01298   0.00702  -0.0749   0.6742   0.8827
   2.750   0.7146   0.01297   0.00699  -0.0748   0.6570   0.8876
   3.000   0.7425   0.01298   0.00697  -0.0748   0.6384   0.8919
   3.250   0.7667   0.01295   0.00691  -0.0739   0.6188   0.8962
   3.500   0.7928   0.01300   0.00689  -0.0734   0.5976   0.9011
   3.750   0.8204   0.01310   0.00695  -0.0735   0.5720   0.9060
   4.000   0.8423   0.01314   0.00693  -0.0721   0.5459   0.9109
   4.250   0.8665   0.01331   0.00699  -0.0714   0.5152   0.9163
   4.500   0.8909   0.01356   0.00711  -0.0709   0.4810   0.9212
   4.750   0.9110   0.01380   0.00722  -0.0694   0.4452   0.9268
   5.000   0.9334   0.01422   0.00747  -0.0687   0.4055   0.9330
   5.250   0.9512   0.01458   0.00767  -0.0669   0.3659   0.9395
   5.500   0.9711   0.01514   0.00800  -0.0659   0.3237   0.9462
   5.750   0.9879   0.01564   0.00833  -0.0641   0.2883   0.9543
   6.000   1.0055   0.01622   0.00873  -0.0626   0.2593   0.9638
   6.250   1.0254   0.01674   0.00916  -0.0616   0.2353   0.9751
   6.500   1.0486   0.01736   0.00967  -0.0613   0.2159   0.9999
   6.750   1.0749   0.01816   0.01040  -0.0619   0.2002   1.0000
   7.000   1.1015   0.01894   0.01113  -0.0625   0.1875   1.0000
   7.250   1.1274   0.01977   0.01191  -0.0629   0.1770   1.0000
   7.500   1.1533   0.02057   0.01266  -0.0633   0.1679   1.0000
   7.750   1.1795   0.02137   0.01350  -0.0637   0.1603   1.0000
   8.000   1.2049   0.02221   0.01430  -0.0640   0.1538   1.0000
   8.250   1.2303   0.02316   0.01527  -0.0643   0.1480   1.0000
   8.500   1.2550   0.02387   0.01604  -0.0644   0.1417   1.0000
   8.750   1.2786   0.02493   0.01700  -0.0645   0.1355   1.0000
   9.000   1.3008   0.02551   0.01774  -0.0642   0.1297   1.0000
   9.250   1.3223   0.02632   0.01855  -0.0639   0.1247   1.0000
   9.500   1.3446   0.02740   0.01965  -0.0637   0.1203   1.0000
   9.750   1.3635   0.02812   0.02051  -0.0628   0.1160   1.0000
  10.000   1.3805   0.02891   0.02134  -0.0617   0.1120   1.0000
  10.250   1.4006   0.03015   0.02253  -0.0613   0.1077   1.0000
  10.500   1.4138   0.03091   0.02352  -0.0596   0.1041   1.0000
  10.750   1.4274   0.03178   0.02448  -0.0582   0.1000   1.0000
  11.000   1.4417   0.03292   0.02557  -0.0571   0.0961   1.0000
  11.250   1.4530   0.03410   0.02695  -0.0556   0.0922   1.0000
  11.500   1.4622   0.03520   0.02818  -0.0540   0.0878   1.0000
  11.750   1.4717   0.03657   0.02950  -0.0527   0.0836   1.0000
  12.000   1.4779   0.03811   0.03126  -0.0511   0.0792   1.0000
  12.250   1.4841   0.03961   0.03284  -0.0498   0.0750   1.0000
  12.500   1.4901   0.04156   0.03476  -0.0485   0.0711   1.0000
  12.750   1.4940   0.04353   0.03697  -0.0473   0.0675   1.0000
  13.000   1.4986   0.04549   0.03901  -0.0463   0.0644   1.0000
  13.250   1.5037   0.04767   0.04112  -0.0452   0.0617   1.0000
  13.500   1.5055   0.05019   0.04387  -0.0442   0.0596   1.0000
  13.750   1.5070   0.05272   0.04659  -0.0434   0.0575   1.0000
  14.000   1.5088   0.05522   0.04921  -0.0428   0.0557   1.0000
  14.250   1.5107   0.05772   0.05176  -0.0424   0.0541   1.0000
  14.500   1.5142   0.06029   0.05431  -0.0416   0.0524   1.0000
  14.750   1.5109   0.06364   0.05788  -0.0413   0.0513   1.0000
  15.000   1.5051   0.06730   0.06178  -0.0413   0.0504   1.0000
  15.250   1.4986   0.07120   0.06590  -0.0415   0.0495   1.0000
  15.500   1.4915   0.07528   0.07018  -0.0421   0.0486   1.0000
  15.750   1.4840   0.07955   0.07463  -0.0429   0.0478   1.0000
  16.000   1.4763   0.08398   0.07922  -0.0440   0.0471   1.0000
  16.250   1.4695   0.08838   0.08375  -0.0453   0.0464   1.0000
  16.500   1.4645   0.09257   0.08803  -0.0466   0.0457   1.0000
  16.750   1.4615   0.09643   0.09194  -0.0477   0.0448   1.0000
  17.000   1.4503   0.10174   0.09736  -0.0493   0.0441   1.0000
  17.250   1.4295   0.10914   0.10501  -0.0532   0.0439   1.0000
  17.500   1.4055   0.11758   0.11370  -0.0581   0.0437   1.0000
  17.750   1.3777   0.12722   0.12361  -0.0642   0.0437   1.0000
  18.000   1.3433   0.13894   0.13558  -0.0721   0.0438   1.0000
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