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NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
Reynolds number: 100,000
Max Cl/Cd: 49.21 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413mod-il-100000-n5.txt
Download as CSV file: xf-ls413mod-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4839   0.09284   0.08734  -0.0417   1.0000   0.0392
 -10.750  -0.4951   0.08530   0.07986  -0.0463   1.0000   0.0387
 -10.500  -0.5322   0.07194   0.06645  -0.0566   1.0000   0.0375
 -10.250  -0.5781   0.06356   0.05792  -0.0612   1.0000   0.0367
 -10.000  -0.6130   0.05879   0.05300  -0.0609   1.0000   0.0363
  -9.750  -0.6304   0.05511   0.04912  -0.0599   1.0000   0.0363
  -9.500  -0.6386   0.05210   0.04593  -0.0585   1.0000   0.0364
  -9.250  -0.6418   0.04941   0.04304  -0.0569   1.0000   0.0367
  -9.000  -0.6417   0.04680   0.04021  -0.0554   1.0000   0.0370
  -8.750  -0.6385   0.04423   0.03739  -0.0539   1.0000   0.0373
  -8.500  -0.6320   0.04169   0.03456  -0.0527   1.0000   0.0375
  -8.250  -0.6223   0.03920   0.03175  -0.0517   1.0000   0.0377
  -8.000  -0.5942   0.03624   0.02835  -0.0539   0.9962   0.0379
  -7.750  -0.5619   0.03368   0.02539  -0.0564   0.9920   0.0382
  -7.500  -0.5295   0.03153   0.02290  -0.0584   0.9873   0.0387
  -7.250  -0.4954   0.02966   0.02074  -0.0604   0.9835   0.0393
  -7.000  -0.4630   0.02808   0.01890  -0.0619   0.9787   0.0400
  -6.750  -0.4297   0.02673   0.01733  -0.0633   0.9740   0.0410
  -6.500  -0.3947   0.02554   0.01610  -0.0653   0.9703   0.0427
  -6.250  -0.3634   0.02463   0.01517  -0.0666   0.9645   0.0446
  -6.000  -0.3296   0.02368   0.01416  -0.0681   0.9597   0.0465
  -5.750  -0.2932   0.02272   0.01313  -0.0700   0.9561   0.0485
  -5.500  -0.2618   0.02184   0.01223  -0.0712   0.9499   0.0506
  -5.250  -0.2268   0.02105   0.01147  -0.0732   0.9448   0.0543
  -5.000  -0.1892   0.02031   0.01069  -0.0755   0.9410   0.0605
  -4.750  -0.1575   0.01964   0.01001  -0.0767   0.9340   0.0684
  -4.500  -0.1223   0.01885   0.00933  -0.0787   0.9286   0.0857
  -4.250  -0.0844   0.01781   0.00869  -0.0814   0.9247   0.1492
  -4.000  -0.0525   0.01662   0.00825  -0.0836   0.9174   0.3007
  -3.750  -0.0206   0.01564   0.00840  -0.0847   0.9119   0.5258
  -3.500   0.0065   0.01583   0.00884  -0.0835   0.9053   0.6213
  -3.250   0.0341   0.01612   0.00913  -0.0826   0.8972   0.6705
  -3.000   0.0637   0.01640   0.00935  -0.0818   0.8915   0.7017
  -2.750   0.0866   0.01670   0.00960  -0.0799   0.8818   0.7222
  -2.500   0.1151   0.01686   0.00968  -0.0791   0.8758   0.7386
  -2.250   0.1392   0.01701   0.00977  -0.0778   0.8658   0.7515
  -2.000   0.1705   0.01702   0.00966  -0.0779   0.8595   0.7640
  -1.750   0.1919   0.01714   0.00976  -0.0760   0.8492   0.7727
  -1.500   0.2242   0.01706   0.00956  -0.0766   0.8426   0.7816
  -1.250   0.2482   0.01709   0.00955  -0.0755   0.8322   0.7872
  -1.000   0.2796   0.01701   0.00939  -0.0760   0.8249   0.7950
  -0.750   0.3043   0.01704   0.00938  -0.0750   0.8150   0.8011
  -0.500   0.3325   0.01700   0.00929  -0.0748   0.8072   0.8079
  -0.250   0.3611   0.01699   0.00925  -0.0750   0.7977   0.8144
   0.000   0.3871   0.01696   0.00919  -0.0742   0.7888   0.8194
   0.250   0.4158   0.01692   0.00911  -0.0743   0.7793   0.8254
   0.500   0.4435   0.01691   0.00908  -0.0742   0.7686   0.8309
   0.750   0.4698   0.01682   0.00896  -0.0734   0.7578   0.8358
   1.000   0.4982   0.01676   0.00886  -0.0733   0.7452   0.8412
   1.250   0.5263   0.01672   0.00880  -0.0732   0.7309   0.8461
   1.500   0.5515   0.01667   0.00874  -0.0724   0.7166   0.8503
   1.750   0.5788   0.01664   0.00869  -0.0721   0.7024   0.8553
   2.000   0.6084   0.01664   0.00868  -0.0725   0.6878   0.8604
   2.250   0.6332   0.01660   0.00864  -0.0715   0.6725   0.8647
   2.500   0.6593   0.01658   0.00859  -0.0709   0.6535   0.8697
   2.750   0.6874   0.01660   0.00856  -0.0709   0.6322   0.8751
   3.000   0.7117   0.01660   0.00853  -0.0699   0.6105   0.8796
   3.250   0.7371   0.01666   0.00856  -0.0693   0.5882   0.8846
   3.500   0.7642   0.01678   0.00862  -0.0691   0.5644   0.8900
   3.750   0.7875   0.01688   0.00869  -0.0681   0.5386   0.8950
   4.000   0.8118   0.01705   0.00878  -0.0673   0.5109   0.9006
   4.250   0.8367   0.01730   0.00894  -0.0669   0.4801   0.9061
   4.500   0.8581   0.01755   0.00908  -0.0656   0.4492   0.9120
   4.750   0.8808   0.01793   0.00932  -0.0648   0.4156   0.9186
   5.000   0.9011   0.01831   0.00959  -0.0636   0.3819   0.9253
   5.250   0.9224   0.01878   0.00994  -0.0626   0.3476   0.9325
   5.500   0.9413   0.01926   0.01028  -0.0613   0.3156   0.9407
   5.750   0.9606   0.01980   0.01069  -0.0601   0.2871   0.9503
   6.000   0.9805   0.02036   0.01117  -0.0591   0.2624   0.9619
   6.250   1.0023   0.02098   0.01170  -0.0587   0.2409   0.9797
   6.500   1.0263   0.02167   0.01234  -0.0587   0.2219   1.0000
   6.750   1.0504   0.02246   0.01310  -0.0588   0.2065   1.0000
   7.000   1.0738   0.02329   0.01388  -0.0589   0.1935   1.0000
   7.250   1.0969   0.02412   0.01469  -0.0588   0.1822   1.0000
   7.500   1.1203   0.02492   0.01552  -0.0588   0.1725   1.0000
   7.750   1.1416   0.02584   0.01640  -0.0585   0.1651   1.0000
   8.000   1.1646   0.02666   0.01732  -0.0583   0.1580   1.0000
   8.250   1.1849   0.02763   0.01826  -0.0578   0.1521   1.0000
   8.500   1.2064   0.02854   0.01926  -0.0574   0.1463   1.0000
   8.750   1.2266   0.02948   0.02026  -0.0569   0.1407   1.0000
   9.000   1.2450   0.03058   0.02128  -0.0562   0.1363   1.0000
   9.250   1.2652   0.03154   0.02242  -0.0555   0.1320   1.0000
   9.500   1.2834   0.03256   0.02355  -0.0546   0.1276   1.0000
   9.750   1.2991   0.03365   0.02463  -0.0536   0.1231   1.0000
  10.000   1.3144   0.03474   0.02588  -0.0525   0.1180   1.0000
  10.250   1.3275   0.03582   0.02707  -0.0513   0.1127   1.0000
  10.750   1.3523   0.03831   0.02978  -0.0490   0.1041   1.0000
  11.000   1.3635   0.03963   0.03125  -0.0478   0.0999   1.0000
  11.250   1.3728   0.04104   0.03271  -0.0466   0.0965   1.0000
  11.500   1.3822   0.04262   0.03443  -0.0455   0.0929   1.0000
  11.750   1.3906   0.04427   0.03630  -0.0444   0.0890   1.0000
  12.000   1.3969   0.04601   0.03817  -0.0434   0.0856   1.0000
  12.250   1.4018   0.04792   0.04007  -0.0425   0.0829   1.0000
  12.500   1.4067   0.05010   0.04256  -0.0417   0.0793   1.0000
  12.750   1.4097   0.05238   0.04501  -0.0409   0.0760   1.0000
  13.000   1.4111   0.05478   0.04751  -0.0404   0.0733   1.0000
  13.250   1.4113   0.05746   0.05028  -0.0400   0.0708   1.0000
  13.500   1.4099   0.06055   0.05365  -0.0398   0.0678   1.0000
  13.750   1.4072   0.06377   0.05706  -0.0398   0.0652   1.0000
  14.000   1.4039   0.06709   0.06049  -0.0400   0.0632   1.0000
  14.250   1.4002   0.07051   0.06397  -0.0404   0.0616   1.0000
  14.500   1.3923   0.07482   0.06852  -0.0411   0.0598   1.0000
  14.750   1.3823   0.07960   0.07356  -0.0422   0.0581   1.0000
  15.000   1.3716   0.08465   0.07882  -0.0438   0.0565   1.0000
  15.250   1.3607   0.08990   0.08424  -0.0458   0.0552   1.0000
  15.500   1.3502   0.09527   0.08974  -0.0480   0.0540   1.0000
  15.750   1.3405   0.10063   0.09520  -0.0505   0.0530   1.0000
  16.000   1.3318   0.10590   0.10053  -0.0529   0.0520   1.0000
  16.250   1.3066   0.11492   0.10986  -0.0580   0.0514   1.0000
  16.500   1.2756   0.12573   0.12094  -0.0645   0.0509   1.0000
  16.750   1.2255   0.14191   0.13742  -0.0751   0.0509   1.0000
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