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LA2573A (la2573a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LA2573A (la2573a-il)
Reynolds number: 50,000
Max Cl/Cd: 13.45 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-la2573a-il-50000-n5.txt
Download as CSV file: xf-la2573a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LA2573A                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4220   0.10877   0.10141   0.0164   0.6125   0.1582
  -8.250  -0.4202   0.10553   0.09817   0.0145   0.6090   0.1616
  -7.750  -0.4538   0.08910   0.08161  -0.0013   0.6072   0.0912
  -7.250  -0.4726   0.07887   0.07113  -0.0065   0.6028   0.0819
  -7.000  -0.4649   0.07540   0.06764  -0.0072   0.5987   0.0807
  -6.750  -0.4602   0.07172   0.06384  -0.0080   0.5951   0.0798
  -6.500  -0.4551   0.06805   0.06000  -0.0086   0.5918   0.0794
  -6.250  -0.4483   0.06455   0.05627  -0.0089   0.5887   0.0794
  -6.000  -0.4393   0.06122   0.05267  -0.0089   0.5860   0.0793
  -5.750  -0.4273   0.05803   0.04920  -0.0089   0.5831   0.0792
  -5.500  -0.4129   0.05496   0.04587  -0.0089   0.5797   0.0787
  -5.250  -0.3969   0.05209   0.04269  -0.0087   0.5763   0.0782
  -5.000  -0.3795   0.04948   0.03974  -0.0082   0.5729   0.0779
  -4.750  -0.3608   0.04712   0.03701  -0.0075   0.5697   0.0779
  -4.500  -0.3409   0.04512   0.03463  -0.0067   0.5667   0.0789
  -4.250  -0.3193   0.04328   0.03240  -0.0061   0.5636   0.0804
  -4.000  -0.2955   0.04155   0.03028  -0.0059   0.5599   0.0817
  -3.750  -0.2707   0.03998   0.02833  -0.0056   0.5565   0.0825
  -3.500  -0.2450   0.03860   0.02675  -0.0054   0.5533   0.0832
  -3.250  -0.2188   0.03744   0.02547  -0.0052   0.5502   0.0845
  -3.000  -0.1928   0.03651   0.02439  -0.0048   0.5473   0.0867
  -2.750  -0.1659   0.03567   0.02333  -0.0045   0.5445   0.0897
  -2.500  -0.1363   0.03495   0.02241  -0.0049   0.5406   0.0923
  -2.250  -0.1066   0.03421   0.02166  -0.0054   0.5372   0.0944
  -2.000  -0.0769   0.03367   0.02112  -0.0057   0.5340   0.0977
  -1.750  -0.0463   0.03324   0.02058  -0.0059   0.5309   0.1028
  -1.500  -0.0154   0.03276   0.02005  -0.0062   0.5280   0.1076
  -1.250   0.0134   0.03238   0.01960  -0.0060   0.5256   0.1130
  -1.000   0.0423   0.03232   0.01959  -0.0068   0.5219   0.1208
  -0.750   0.0691   0.03231   0.01964  -0.0072   0.5184   0.1305
  -0.500   0.0935   0.03224   0.01967  -0.0070   0.5151   0.1434
  -0.250   0.1167   0.03208   0.01963  -0.0065   0.5120   0.1666
   0.000   0.1362   0.03141   0.01953  -0.0054   0.5094   0.2419
   0.500   0.3263   0.03095   0.02078  -0.0268   0.5010   1.0000
   0.750   0.3489   0.03180   0.02155  -0.0271   0.4970   1.0000
   1.000   0.3705   0.03252   0.02217  -0.0269   0.4935   1.0000
   1.250   0.3914   0.03315   0.02269  -0.0263   0.4905   1.0000
   1.500   0.4121   0.03373   0.02314  -0.0254   0.4881   1.0000
   1.750   0.4325   0.03426   0.02353  -0.0243   0.4861   1.0000
   2.000   0.4516   0.03570   0.02501  -0.0250   0.4817   1.0000
   2.250   0.4691   0.03717   0.02652  -0.0255   0.4768   1.0000
   2.500   0.4864   0.03830   0.02762  -0.0250   0.4731   1.0000
   2.750   0.5041   0.03917   0.02843  -0.0241   0.4700   1.0000
   3.000   0.5226   0.03982   0.02900  -0.0227   0.4675   1.0000
   3.250   0.5420   0.04031   0.02940  -0.0211   0.4655   1.0000
   3.500   0.5433   0.04360   0.03286  -0.0226   0.4579   1.0000
   3.750   0.5535   0.04516   0.03443  -0.0219   0.4534   1.0000
   4.000   0.5680   0.04613   0.03536  -0.0205   0.4501   1.0000
   4.250   0.5853   0.04680   0.03598  -0.0188   0.4475   1.0000
   4.750   0.5779   0.05218   0.04142  -0.0179   0.4351   1.0000
   5.000   0.5889   0.05338   0.04260  -0.0165   0.4312   1.0000
   5.250   0.6068   0.05407   0.04324  -0.0148   0.4285   1.0000
   5.500   0.6271   0.05461   0.04374  -0.0131   0.4264   1.0000
   5.750   0.5863   0.05966   0.04882  -0.0131   0.4155   1.0000
   6.000   0.5998   0.06072   0.04985  -0.0117   0.4118   1.0000
   6.250   0.6222   0.06132   0.05044  -0.0104   0.4092   1.0000
   6.500   0.5891   0.06508   0.05415  -0.0089   0.4006   1.0000
   6.750   0.5981   0.06654   0.05561  -0.0079   0.3958   1.0000
   7.000   0.6189   0.06737   0.05643  -0.0069   0.3927   1.0000
   7.250   0.6085   0.07022   0.05927  -0.0064   0.3856   1.0000
   7.500   0.6139   0.07207   0.06114  -0.0058   0.3799   1.0000
   7.750   0.6342   0.07298   0.06205  -0.0049   0.3763   1.0000
   8.000   0.6292   0.07570   0.06478  -0.0048   0.3695   1.0000
   8.250   0.6364   0.07754   0.06664  -0.0044   0.3635   1.0000
   8.500   0.6584   0.07833   0.06747  -0.0036   0.3601   1.0000
   9.000   0.6638   0.08287   0.07206  -0.0034   0.3469   1.0000
   9.250   0.6896   0.08334   0.07256  -0.0024   0.3438   1.0000
   9.500   0.6747   0.08716   0.07642  -0.0033   0.3342   1.0000
   9.750   0.6974   0.08779   0.07710  -0.0024   0.3301   1.0000
  10.000   0.6900   0.09117   0.08052  -0.0031   0.3217   1.0000
  10.250   0.7085   0.09209   0.08149  -0.0025   0.3165   1.0000
  10.500   0.7083   0.09490   0.08435  -0.0029   0.3090   1.0000
  10.750   0.7221   0.09625   0.08576  -0.0025   0.3028   1.0000
  11.000   0.7270   0.09856   0.08812  -0.0027   0.2956   1.0000
  11.250   0.7380   0.10015   0.08980  -0.0025   0.2886   1.0000
  11.500   0.7431   0.10241   0.09210  -0.0028   0.2809   1.0000
  11.750   0.7567   0.10360   0.09337  -0.0024   0.2738   1.0000
  12.000   0.7576   0.10635   0.09617  -0.0030   0.2649   1.0000
  12.250   0.7785   0.10645   0.09637  -0.0020   0.2586   1.0000
  12.750   0.8043   0.10844   0.09850  -0.0013   0.2431   1.0000
  13.000   0.7976   0.11235   0.10247  -0.0027   0.2317   1.0000
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