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NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)
Reynolds number: 100,000
Max Cl/Cd: 41.01 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls417-il-100000-n5.txt
Download as CSV file: xf-ls417-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5760   0.08280   0.07667  -0.0793   1.0000   0.0348
 -13.250  -0.6422   0.07102   0.06452  -0.0857   1.0000   0.0342
 -13.000  -0.6812   0.06569   0.05899  -0.0860   1.0000   0.0340
 -12.750  -0.7160   0.06250   0.05566  -0.0834   1.0000   0.0339
 -12.500  -0.7435   0.05981   0.05282  -0.0810   0.9983   0.0339
 -12.250  -0.7444   0.05603   0.04877  -0.0835   0.9918   0.0341
 -12.000  -0.7420   0.05279   0.04529  -0.0853   0.9845   0.0343
 -11.750  -0.7358   0.04990   0.04215  -0.0869   0.9781   0.0347
 -11.500  -0.7278   0.04739   0.03940  -0.0879   0.9711   0.0351
 -11.250  -0.7153   0.04500   0.03675  -0.0892   0.9656   0.0359
 -11.000  -0.7043   0.04280   0.03424  -0.0895   0.9583   0.0367
 -10.750  -0.6860   0.04061   0.03171  -0.0906   0.9540   0.0377
 -10.500  -0.6637   0.03927   0.03033  -0.0914   0.9497   0.0385
 -10.250  -0.6455   0.03798   0.02894  -0.0912   0.9436   0.0393
 -10.000  -0.6214   0.03651   0.02731  -0.0918   0.9395   0.0402
  -9.750  -0.5945   0.03504   0.02565  -0.0926   0.9364   0.0413
  -9.500  -0.5729   0.03386   0.02432  -0.0923   0.9317   0.0424
  -9.250  -0.5535   0.03295   0.02343  -0.0918   0.9264   0.0433
  -9.000  -0.5299   0.03200   0.02243  -0.0919   0.9225   0.0449
  -8.750  -0.5038   0.03104   0.02132  -0.0924   0.9194   0.0472
  -8.500  -0.4786   0.03011   0.02042  -0.0930   0.9164   0.0494
  -8.250  -0.4645   0.02951   0.01977  -0.0913   0.9095   0.0516
  -8.000  -0.4435   0.02870   0.01893  -0.0909   0.9050   0.0541
  -7.750  -0.4206   0.02786   0.01809  -0.0910   0.9016   0.0571
  -7.500  -0.3962   0.02703   0.01723  -0.0913   0.8989   0.0613
  -7.250  -0.3784   0.02645   0.01664  -0.0905   0.8943   0.0667
  -7.000  -0.3619   0.02589   0.01611  -0.0894   0.8891   0.0731
  -6.750  -0.3398   0.02523   0.01551  -0.0893   0.8851   0.0828
  -6.500  -0.3146   0.02453   0.01490  -0.0897   0.8820   0.0979
  -6.250  -0.2876   0.02381   0.01430  -0.0904   0.8795   0.1210
  -6.000  -0.2645   0.02319   0.01385  -0.0905   0.8762   0.1516
  -5.750  -0.2484   0.02271   0.01364  -0.0895   0.8708   0.1942
  -5.500  -0.2265   0.02188   0.01329  -0.0899   0.8671   0.2743
  -5.250  -0.2007   0.02104   0.01297  -0.0909   0.8642   0.3726
  -5.000  -0.1739   0.02065   0.01302  -0.0909   0.8617   0.4570
  -4.750  -0.1485   0.02092   0.01360  -0.0894   0.8594   0.5185
  -4.500  -0.1221   0.02136   0.01410  -0.0883   0.8570   0.5657
  -4.250  -0.1055   0.02199   0.01472  -0.0863   0.8512   0.5973
  -4.000  -0.0793   0.02237   0.01500  -0.0862   0.8475   0.6255
  -3.750  -0.0517   0.02275   0.01528  -0.0860   0.8444   0.6440
  -3.500  -0.0257   0.02322   0.01570  -0.0848   0.8417   0.6565
  -3.250   0.0019   0.02363   0.01603  -0.0840   0.8396   0.6693
  -3.000   0.0317   0.02396   0.01628  -0.0839   0.8379   0.6841
  -2.750   0.0394   0.02479   0.01712  -0.0798   0.8309   0.6920
  -2.500   0.0643   0.02503   0.01728  -0.0797   0.8268   0.7031
  -2.250   0.0875   0.02531   0.01753  -0.0783   0.8236   0.7080
  -2.000   0.1168   0.02538   0.01753  -0.0785   0.8211   0.7147
  -1.750   0.1500   0.02533   0.01739  -0.0798   0.8192   0.7220
  -1.500   0.1780   0.02545   0.01747  -0.0793   0.8174   0.7266
  -1.250   0.1849   0.02613   0.01817  -0.0764   0.8089   0.7333
  -1.000   0.2124   0.02624   0.01824  -0.0768   0.8051   0.7403
  -0.750   0.2377   0.02636   0.01835  -0.0759   0.8021   0.7447
  -0.500   0.2689   0.02633   0.01828  -0.0764   0.7998   0.7501
  -0.250   0.3070   0.02616   0.01805  -0.0788   0.7980   0.7563
   0.000   0.3113   0.02685   0.01879  -0.0750   0.7886   0.7597
   0.250   0.3376   0.02687   0.01881  -0.0747   0.7842   0.7633
   0.500   0.3710   0.02669   0.01862  -0.0756   0.7812   0.7673
   0.750   0.4094   0.02640   0.01830  -0.0776   0.7790   0.7715
   1.250   0.4490   0.02687   0.01883  -0.0755   0.7647   0.7778
   1.500   0.4833   0.02655   0.01852  -0.0764   0.7613   0.7806
   1.750   0.5239   0.02596   0.01792  -0.0781   0.7585   0.7833
   2.000   0.5376   0.02634   0.01835  -0.0763   0.7462   0.7871
   2.250   0.5816   0.02553   0.01753  -0.0787   0.7412   0.7902
   2.500   0.6033   0.02547   0.01752  -0.0776   0.7313   0.7924
   2.750   0.6355   0.02488   0.01696  -0.0777   0.7234   0.7946
   3.000   0.6610   0.02457   0.01669  -0.0769   0.7132   0.7973
   3.500   0.7157   0.02389   0.01611  -0.0763   0.6903   0.8027
   3.750   0.7551   0.02319   0.01541  -0.0778   0.6817   0.8051
   4.000   0.7744   0.02332   0.01562  -0.0767   0.6659   0.8082
   4.250   0.7904   0.02332   0.01570  -0.0745   0.6491   0.8107
   4.500   0.8099   0.02318   0.01560  -0.0727   0.6298   0.8134
   4.750   0.8270   0.02315   0.01560  -0.0708   0.6056   0.8162
   5.000   0.8554   0.02276   0.01515  -0.0704   0.5729   0.8188
   5.250   0.8904   0.02229   0.01443  -0.0709   0.5254   0.8212
   5.500   0.9173   0.02237   0.01414  -0.0705   0.4692   0.8239
   5.750   0.9303   0.02296   0.01442  -0.0681   0.4210   0.8264
   6.000   0.9395   0.02374   0.01496  -0.0653   0.3787   0.8292
   6.250   0.9502   0.02464   0.01565  -0.0630   0.3405   0.8325
   6.500   0.9623   0.02562   0.01643  -0.0612   0.3075   0.8361
   6.750   0.9769   0.02659   0.01725  -0.0600   0.2782   0.8396
   7.000   0.9914   0.02759   0.01810  -0.0588   0.2540   0.8426
   7.250   1.0043   0.02849   0.01891  -0.0572   0.2345   0.8453
   7.750   1.0337   0.03034   0.02064  -0.0548   0.2028   0.8517
   8.000   1.0505   0.03126   0.02154  -0.0540   0.1902   0.8552
   8.250   1.0667   0.03226   0.02250  -0.0532   0.1797   0.8590
   8.500   1.0798   0.03318   0.02341  -0.0517   0.1708   0.8625
   8.750   1.0948   0.03411   0.02436  -0.0506   0.1632   0.8666
   9.000   1.1099   0.03514   0.02538  -0.0496   0.1563   0.8708
   9.250   1.1263   0.03620   0.02643  -0.0489   0.1502   0.8748
   9.500   1.1407   0.03712   0.02742  -0.0477   0.1445   0.8785
   9.750   1.1540   0.03822   0.02848  -0.0466   0.1399   0.8827
  10.000   1.1710   0.03921   0.02955  -0.0458   0.1351   0.8872
  10.250   1.1867   0.04023   0.03064  -0.0450   0.1307   0.8917
  10.500   1.1997   0.04130   0.03170  -0.0438   0.1271   0.8968
  10.750   1.2154   0.04234   0.03282  -0.0429   0.1234   0.9027
  11.000   1.2293   0.04337   0.03396  -0.0418   0.1197   0.9087
  11.250   1.2423   0.04446   0.03509  -0.0406   0.1165   0.9156
  11.500   1.2551   0.04557   0.03618  -0.0395   0.1138   0.9228
  11.750   1.2675   0.04670   0.03751  -0.0383   0.1104   0.9313
  12.000   1.2782   0.04785   0.03877  -0.0370   0.1074   0.9422
  12.500   1.2986   0.05027   0.04126  -0.0351   0.1024   1.0000
  12.750   1.3124   0.05196   0.04315  -0.0350   0.0994   1.0000
  13.000   1.3251   0.05367   0.04497  -0.0349   0.0966   1.0000
  13.250   1.3375   0.05536   0.04667  -0.0348   0.0944   1.0000
  13.500   1.3497   0.05715   0.04851  -0.0347   0.0922   1.0000
  13.750   1.3579   0.05929   0.05087  -0.0344   0.0897   1.0000
  14.000   1.3658   0.06139   0.05311  -0.0342   0.0874   1.0000
  14.250   1.3744   0.06340   0.05517  -0.0340   0.0855   1.0000
  14.500   1.3851   0.06524   0.05695  -0.0339   0.0838   1.0000
  14.750   1.3857   0.06821   0.06023  -0.0337   0.0818   1.0000
  15.000   1.3872   0.07107   0.06330  -0.0336   0.0798   1.0000
  15.250   1.3897   0.07382   0.06618  -0.0336   0.0781   1.0000
  15.500   1.3945   0.07629   0.06870  -0.0337   0.0766   1.0000
  15.750   1.4000   0.07873   0.07114  -0.0338   0.0752   1.0000
  16.000   1.3907   0.08315   0.07590  -0.0344   0.0737   1.0000
  16.250   1.3828   0.08749   0.08049  -0.0352   0.0722   1.0000
  16.500   1.3763   0.09173   0.08491  -0.0362   0.0709   1.0000
  16.750   1.3722   0.09569   0.08901  -0.0374   0.0697   1.0000
  17.000   1.3736   0.09890   0.09227  -0.0384   0.0686   1.0000
  17.250   1.3708   0.10283   0.09628  -0.0398   0.0676   1.0000
  17.500   1.3437   0.11103   0.10487  -0.0436   0.0666   1.0000
  17.750   1.3112   0.12078   0.11499  -0.0490   0.0658   1.0000
  18.000   1.2530   0.13684   0.13149  -0.0593   0.0652   1.0000
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