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LIEBECK LA5055 AIRFOIL (la5055-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LIEBECK LA5055 AIRFOIL (la5055-il)
Reynolds number: 500,000
Max Cl/Cd: 116.27 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-la5055-il-500000.txt
Download as CSV file: xf-la5055-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LIEBECK LA5055 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1601   0.10541   0.10130  -0.0311   0.5572   0.0373
  -9.250  -0.1533   0.10256   0.09847  -0.0326   0.5566   0.0380
  -8.750  -0.1753   0.09322   0.08918  -0.0420   0.5558   0.0396
  -8.500  -0.1644   0.09028   0.08626  -0.0421   0.5552   0.0398
  -8.250  -0.1520   0.08806   0.08405  -0.0422   0.5546   0.0399
  -8.000  -0.1405   0.08591   0.08191  -0.0425   0.5541   0.0401
  -7.750  -0.1301   0.08374   0.07976  -0.0430   0.5535   0.0404
  -7.500  -0.1213   0.08151   0.07755  -0.0438   0.5528   0.0408
  -7.250  -0.1150   0.07906   0.07512  -0.0449   0.5522   0.0411
  -7.000  -0.1108   0.07644   0.07251  -0.0461   0.5515   0.0417
  -6.750  -0.1102   0.07362   0.06972  -0.0475   0.5508   0.0424
  -6.500  -0.1530   0.06109   0.05705  -0.0642   0.5507   0.0445
  -6.250  -0.1391   0.05917   0.05515  -0.0639   0.5500   0.0447
  -6.000  -0.1246   0.05722   0.05319  -0.0642   0.5492   0.0449
  -5.750  -0.1091   0.05540   0.05133  -0.0645   0.5484   0.0452
  -5.500  -0.0933   0.05325   0.04913  -0.0654   0.5476   0.0455
  -5.250  -0.0767   0.05106   0.04688  -0.0664   0.5467   0.0461
  -5.000  -0.0686   0.04302   0.03821  -0.0708   0.5460   0.0500
  -4.750  -0.0480   0.04166   0.03689  -0.0710   0.5448   0.0503
  -4.500  -0.0260   0.04024   0.03548  -0.0712   0.5443   0.0507
  -4.250  -0.0035   0.03892   0.03415  -0.0714   0.5437   0.0513
  -4.000   0.0193   0.03738   0.03254  -0.0717   0.5430   0.0521
  -3.750   0.0405   0.03364   0.02824  -0.0720   0.5423   0.0562
  -3.500   0.0649   0.03237   0.02700  -0.0721   0.5413   0.0567
  -3.250   0.0898   0.03128   0.02589  -0.0723   0.5401   0.0573
  -3.000   0.1152   0.03018   0.02472  -0.0723   0.5387   0.0585
  -2.750   0.1408   0.02829   0.02235  -0.0719   0.5373   0.0630
  -2.500   0.1668   0.02710   0.02118  -0.0720   0.5358   0.0637
  -2.250   0.1934   0.02624   0.02030  -0.0720   0.5346   0.0649
  -1.750   0.2480   0.02157   0.01473  -0.0707   0.5328   0.0548
  -1.500   0.2755   0.02038   0.01342  -0.0705   0.5320   0.0537
  -1.250   0.3035   0.01949   0.01240  -0.0704   0.5311   0.0534
  -1.000   0.3318   0.01888   0.01167  -0.0702   0.5303   0.0538
  -0.750   0.3601   0.01832   0.01101  -0.0701   0.5295   0.0539
  -0.500   0.3882   0.01791   0.01052  -0.0699   0.5284   0.0541
  -0.250   0.4157   0.01771   0.01029  -0.0698   0.5267   0.0544
   0.000   0.4443   0.01724   0.00981  -0.0697   0.5254   0.0549
   0.250   0.4728   0.01690   0.00947  -0.0697   0.5237   0.0553
   0.500   0.5007   0.01647   0.00905  -0.0696   0.5221   0.0561
   0.750   0.5287   0.01609   0.00874  -0.0695   0.5203   0.0573
   1.000   0.5570   0.01587   0.00854  -0.0695   0.5189   0.0585
   1.250   0.5853   0.01563   0.00832  -0.0694   0.5176   0.0596
   1.500   0.6138   0.01541   0.00809  -0.0694   0.5163   0.0607
   1.750   0.6425   0.01521   0.00789  -0.0693   0.5152   0.0618
   2.000   0.6709   0.01494   0.00762  -0.0693   0.5142   0.0635
   2.250   0.6998   0.01472   0.00741  -0.0693   0.5131   0.0658
   2.500   0.7288   0.01458   0.00725  -0.0693   0.5119   0.0689
   2.750   0.7571   0.01454   0.00720  -0.0693   0.5105   0.0731
   3.000   0.7851   0.01453   0.00725  -0.0694   0.5093   0.0792
   3.250   0.8128   0.01438   0.00728  -0.0694   0.5080   0.1137
   3.500   0.8547   0.01238   0.00751  -0.0728   0.5064   1.0000
   3.750   0.8819   0.01247   0.00758  -0.0726   0.5048   1.0000
   4.000   0.9094   0.01254   0.00763  -0.0725   0.5032   1.0000
   4.250   0.9371   0.01258   0.00766  -0.0724   0.5018   1.0000
   4.500   0.9651   0.01260   0.00765  -0.0724   0.5004   1.0000
   4.750   0.9932   0.01260   0.00763  -0.0724   0.4992   1.0000
   5.000   1.0216   0.01257   0.00756  -0.0724   0.4980   1.0000
   5.250   1.0506   0.01244   0.00738  -0.0724   0.4965   1.0000
   5.500   1.0797   0.01230   0.00718  -0.0724   0.4948   1.0000
   5.750   1.1072   0.01234   0.00724  -0.0724   0.4927   1.0000
   6.000   1.1342   0.01241   0.00737  -0.0724   0.4901   1.0000
   6.250   1.1620   0.01239   0.00738  -0.0724   0.4872   1.0000
   6.500   1.1902   0.01233   0.00734  -0.0724   0.4847   1.0000
   6.750   1.2187   0.01224   0.00724  -0.0725   0.4824   1.0000
   7.000   1.2474   0.01211   0.00709  -0.0725   0.4801   1.0000
   7.250   1.2750   0.01212   0.00713  -0.0726   0.4770   1.0000
   7.500   1.3016   0.01227   0.00736  -0.0726   0.4725   1.0000
   7.750   1.3291   0.01227   0.00741  -0.0726   0.4681   1.0000
   8.000   1.3575   0.01215   0.00727  -0.0727   0.4639   1.0000
   8.250   1.3836   0.01236   0.00756  -0.0727   0.4573   1.0000
   8.500   1.4110   0.01232   0.00752  -0.0727   0.4502   1.0000
   8.750   1.4372   0.01239   0.00757  -0.0726   0.4392   1.0000
   9.000   1.4615   0.01257   0.00767  -0.0723   0.4261   1.0000
   9.250   1.4817   0.01306   0.00807  -0.0716   0.4101   1.0000
   9.500   1.4986   0.01380   0.00875  -0.0707   0.3913   1.0000
   9.750   1.4886   0.01627   0.01100  -0.0677   0.3298   1.0000
  10.250   1.3851   0.02807   0.02284  -0.0606   0.3091   1.0000
  10.500   1.3583   0.03194   0.02667  -0.0581   0.3004   1.0000
  10.750   1.3530   0.03433   0.02909  -0.0567   0.2918   1.0000
  11.000   1.3442   0.03699   0.03171  -0.0552   0.2817   1.0000
  11.250   1.3398   0.03957   0.03428  -0.0542   0.2657   1.0000
  11.500   1.3290   0.04281   0.03740  -0.0531   0.2433   1.0000
  11.750   1.3174   0.04625   0.04075  -0.0521   0.2298   1.0000
  12.000   1.3164   0.04873   0.04316  -0.0513   0.2221   1.0000
  12.250   1.3210   0.05068   0.04510  -0.0507   0.2159   1.0000
  12.500   1.3260   0.05265   0.04706  -0.0502   0.2108   1.0000
  12.750   1.3303   0.05467   0.04905  -0.0496   0.2056   1.0000
  13.000   1.3398   0.05620   0.05059  -0.0491   0.2015   1.0000
  13.250   1.3505   0.05766   0.05209  -0.0488   0.1966   1.0000
  13.500   1.3579   0.05942   0.05385  -0.0483   0.1910   1.0000
  13.750   1.3656   0.06120   0.05561  -0.0479   0.1859   1.0000
  14.000   1.3760   0.06277   0.05723  -0.0477   0.1793   1.0000
  14.250   1.3813   0.06484   0.05928  -0.0474   0.1716   1.0000
  14.500   1.3901   0.06658   0.06101  -0.0471   0.1607   1.0000
  14.750   1.3932   0.06894   0.06329  -0.0469   0.1471   1.0000
  15.000   1.3940   0.07157   0.06585  -0.0466   0.1371   1.0000
  15.250   1.3963   0.07406   0.06829  -0.0464   0.1294   1.0000
  15.500   1.4003   0.07637   0.07056  -0.0463   0.1234   1.0000
  15.750   1.4055   0.07855   0.07275  -0.0461   0.1182   1.0000
  16.000   1.4103   0.08083   0.07504  -0.0461   0.1130   1.0000
  16.250   1.4136   0.08330   0.07749  -0.0460   0.1070   1.0000
  16.500   1.4179   0.08568   0.07985  -0.0460   0.0983   1.0000
  16.750   1.4164   0.08881   0.08284  -0.0462   0.0704   1.0000
  17.000   1.4093   0.09265   0.08654  -0.0464   0.0606   1.0000
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