Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 544 AIRFOIL (e544-il)
Reynolds number: 500,000
Max Cl/Cd: 86.21 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e544-il-500000-n5.txt
Download as CSV file: xf-e544-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 544 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.5951   0.09480   0.09219  -0.0578   1.0000   0.0035
 -14.750  -0.6230   0.08302   0.08025  -0.0648   1.0000   0.0034
 -14.500  -0.6568   0.07245   0.06946  -0.0709   1.0000   0.0033
 -14.250  -0.6800   0.06551   0.06234  -0.0740   1.0000   0.0033
 -14.000  -0.7060   0.05912   0.05572  -0.0757   1.0000   0.0033
 -13.750  -0.7238   0.05450   0.05092  -0.0761   1.0000   0.0033
 -13.500  -0.7363   0.05091   0.04716  -0.0758   1.0000   0.0033
 -13.250  -0.7508   0.04730   0.04335  -0.0748   1.0000   0.0033
 -13.000  -0.7652   0.04385   0.03966  -0.0733   1.0000   0.0033
 -12.750  -0.7718   0.04134   0.03698  -0.0716   1.0000   0.0032
 -12.500  -0.7777   0.03895   0.03441  -0.0696   1.0000   0.0033
 -12.250  -0.7676   0.03618   0.03140  -0.0708   0.9973   0.0033
 -12.000  -0.7584   0.03390   0.02893  -0.0707   0.9856   0.0033
 -11.750  -0.7453   0.03188   0.02672  -0.0710   0.9647   0.0034
 -11.500  -0.7172   0.02994   0.02458  -0.0741   0.9518   0.0034
 -11.000  -0.6399   0.02619   0.02040  -0.0838   0.9325   0.0036
 -10.750  -0.5957   0.02463   0.01864  -0.0895   0.9183   0.0037
 -10.500  -0.5572   0.02342   0.01725  -0.0936   0.8984   0.0038
 -10.250  -0.5324   0.02253   0.01617  -0.0947   0.8777   0.0038
 -10.000  -0.5167   0.02167   0.01516  -0.0939   0.8594   0.0039
  -9.750  -0.5027   0.02092   0.01429  -0.0927   0.8440   0.0041
  -9.250  -0.4734   0.01969   0.01287  -0.0899   0.8179   0.0045
  -9.000  -0.4584   0.01913   0.01222  -0.0885   0.8069   0.0048
  -8.750  -0.4435   0.01859   0.01158  -0.0871   0.7968   0.0049
  -8.500  -0.4280   0.01807   0.01098  -0.0857   0.7874   0.0053
  -8.250  -0.4126   0.01757   0.01039  -0.0843   0.7791   0.0055
  -8.000  -0.3979   0.01702   0.00979  -0.0827   0.7706   0.0060
  -7.750  -0.3831   0.01652   0.00922  -0.0811   0.7630   0.0065
  -7.500  -0.3673   0.01607   0.00870  -0.0797   0.7552   0.0072
  -7.250  -0.3517   0.01565   0.00820  -0.0781   0.7477   0.0077
  -7.000  -0.3371   0.01517   0.00769  -0.0765   0.7405   0.0086
  -6.750  -0.3222   0.01476   0.00723  -0.0748   0.7340   0.0103
  -6.500  -0.3085   0.01432   0.00676  -0.0729   0.7279   0.0129
  -6.000  -0.2877   0.01356   0.00598  -0.0676   0.7159   0.0239
  -5.750  -0.2740   0.01317   0.00564  -0.0655   0.7100   0.0363
  -5.500  -0.2585   0.01280   0.00531  -0.0638   0.7042   0.0516
  -5.250  -0.2434   0.01238   0.00498  -0.0620   0.6991   0.0768
  -5.000  -0.2277   0.01191   0.00465  -0.0603   0.6940   0.1137
  -4.750  -0.2134   0.01133   0.00429  -0.0584   0.6890   0.1686
  -4.500  -0.2021   0.01052   0.00383  -0.0563   0.6847   0.2608
  -4.250  -0.1936   0.00931   0.00320  -0.0538   0.6800   0.4028
  -4.000  -0.1825   0.00826   0.00286  -0.0515   0.6751   0.5752
  -3.750  -0.1558   0.00830   0.00292  -0.0513   0.6707   0.6137
  -3.500  -0.1280   0.00840   0.00297  -0.0514   0.6668   0.6331
  -3.250  -0.1000   0.00855   0.00308  -0.0514   0.6627   0.6489
  -3.000  -0.0720   0.00873   0.00318  -0.0515   0.6587   0.6615
  -2.750  -0.0439   0.00900   0.00344  -0.0514   0.6549   0.6707
  -2.500  -0.0159   0.00911   0.00345  -0.0515   0.6512   0.6770
  -2.250   0.0125   0.00909   0.00339  -0.0518   0.6472   0.6782
  -2.000   0.0409   0.00908   0.00333  -0.0521   0.6434   0.6792
  -1.750   0.0691   0.00908   0.00328  -0.0524   0.6400   0.6802
  -1.500   0.0974   0.00909   0.00322  -0.0526   0.6367   0.6811
  -1.250   0.1259   0.00907   0.00318  -0.0530   0.6332   0.6821
  -1.000   0.1542   0.00907   0.00314  -0.0533   0.6294   0.6830
  -0.750   0.1825   0.00908   0.00310  -0.0536   0.6261   0.6841
  -0.500   0.2107   0.00910   0.00307  -0.0539   0.6229   0.6853
  -0.250   0.2390   0.00911   0.00305  -0.0542   0.6197   0.6864
   0.000   0.2674   0.00911   0.00303  -0.0545   0.6163   0.6874
   0.250   0.2957   0.00911   0.00301  -0.0549   0.6128   0.6884
   0.500   0.3238   0.00913   0.00299  -0.0552   0.6095   0.6894
   0.750   0.3519   0.00917   0.00298  -0.0554   0.6063   0.6904
   1.000   0.3802   0.00918   0.00299  -0.0558   0.6030   0.6914
   1.250   0.4084   0.00920   0.00300  -0.0561   0.5992   0.6924
   1.500   0.4362   0.00922   0.00301  -0.0563   0.5950   0.6934
   1.750   0.4636   0.00926   0.00303  -0.0564   0.5908   0.6943
   2.000   0.4913   0.00928   0.00307  -0.0566   0.5863   0.6951
   2.250   0.5189   0.00931   0.00311  -0.0568   0.5816   0.6960
   2.500   0.5463   0.00935   0.00316  -0.0569   0.5772   0.6968
   2.750   0.5736   0.00941   0.00321  -0.0571   0.5729   0.6978
   3.000   0.6009   0.00943   0.00328  -0.0572   0.5677   0.6987
   3.250   0.6278   0.00948   0.00334  -0.0572   0.5622   0.6997
   3.500   0.6546   0.00955   0.00340  -0.0573   0.5572   0.7007
   3.750   0.6817   0.00959   0.00348  -0.0574   0.5514   0.7018
   4.000   0.7080   0.00965   0.00356  -0.0573   0.5453   0.7028
   4.250   0.7344   0.00972   0.00364  -0.0573   0.5389   0.7041
   4.500   0.7603   0.00979   0.00373  -0.0571   0.5312   0.7054
   4.750   0.7860   0.00988   0.00383  -0.0570   0.5234   0.7066
   5.000   0.8111   0.00997   0.00393  -0.0567   0.5141   0.7076
   5.250   0.8361   0.01006   0.00404  -0.0564   0.5040   0.7086
   5.500   0.8598   0.01017   0.00416  -0.0558   0.4923   0.7096
   5.750   0.8823   0.01031   0.00430  -0.0550   0.4775   0.7106
   6.000   0.9035   0.01048   0.00446  -0.0540   0.4592   0.7117
   6.250   0.9217   0.01075   0.00467  -0.0524   0.4359   0.7128
   6.500   0.9377   0.01109   0.00493  -0.0505   0.4088   0.7139
   6.750   0.9510   0.01149   0.00523  -0.0480   0.3810   0.7152
   7.000   0.9606   0.01192   0.00556  -0.0449   0.3542   0.7165
   7.250   0.9701   0.01241   0.00595  -0.0418   0.3286   0.7179
   7.500   0.9806   0.01293   0.00639  -0.0391   0.3047   0.7195
   8.000   0.9995   0.01412   0.00741  -0.0335   0.2575   0.7227
   8.500   1.0154   0.01550   0.00862  -0.0279   0.2131   0.7254
   8.750   1.0238   0.01621   0.00929  -0.0254   0.1945   0.7268
   9.000   1.0308   0.01702   0.01005  -0.0228   0.1760   0.7282
   9.250   1.0374   0.01790   0.01087  -0.0203   0.1574   0.7297
   9.500   1.0451   0.01879   0.01172  -0.0181   0.1416   0.7313
   9.750   1.0532   0.01972   0.01263  -0.0161   0.1281   0.7329
  10.000   1.0610   0.02071   0.01359  -0.0141   0.1149   0.7346
  10.250   1.0690   0.02174   0.01460  -0.0123   0.1036   0.7363
  10.500   1.0771   0.02281   0.01565  -0.0107   0.0927   0.7380
  10.750   1.0856   0.02390   0.01673  -0.0091   0.0830   0.7396
  11.000   1.0933   0.02508   0.01791  -0.0076   0.0738   0.7413
  11.250   1.1000   0.02634   0.01917  -0.0061   0.0648   0.7432
  11.500   1.1066   0.02765   0.02048  -0.0047   0.0572   0.7451
  11.750   1.1145   0.02893   0.02179  -0.0035   0.0501   0.7471
  12.000   1.1221   0.03026   0.02314  -0.0024   0.0446   0.7491
  12.250   1.1286   0.03172   0.02461  -0.0013   0.0392   0.7511
  12.500   1.1362   0.03314   0.02606  -0.0003   0.0347   0.7532
  12.750   1.1433   0.03465   0.02760   0.0006   0.0310   0.7552
  13.000   1.1501   0.03621   0.02920   0.0014   0.0276   0.7571
  13.250   1.1571   0.03778   0.03083   0.0021   0.0248   0.7591
  13.500   1.1634   0.03947   0.03256   0.0028   0.0223   0.7614
  13.750   1.1702   0.04115   0.03431   0.0034   0.0199   0.7638
  14.000   1.1758   0.04300   0.03620   0.0039   0.0179   0.7663
  14.250   1.1823   0.04481   0.03808   0.0043   0.0161   0.7689
  14.500   1.1880   0.04675   0.04009   0.0046   0.0147   0.7715
  14.750   1.1933   0.04878   0.04219   0.0049   0.0133   0.7741
  15.000   1.1984   0.05083   0.04433   0.0051   0.0122   0.7772
  15.250   1.2023   0.05308   0.04665   0.0052   0.0110   0.7806
  15.500   1.2071   0.05532   0.04898   0.0052   0.0099   0.7842
  15.750   1.2104   0.05777   0.05150   0.0051   0.0089   0.7877
  16.000   1.2140   0.06020   0.05403   0.0049   0.0081   0.7914
  16.250   1.2168   0.06280   0.05676   0.0047   0.0076   0.7954
  16.500   1.2194   0.06549   0.05954   0.0043   0.0072   0.7998
  17.000   1.2213   0.07149   0.06575   0.0032   0.0059   0.8090
  17.250   1.2216   0.07464   0.06902   0.0024   0.0055   0.8146
  17.750   1.2192   0.08159   0.07620   0.0005   0.0048   0.8273
  18.000   1.2173   0.08529   0.08004  -0.0006   0.0045   0.8352
  18.250   1.2149   0.08908   0.08399  -0.0018   0.0043   0.8448
  18.500   1.2111   0.09309   0.08815  -0.0032   0.0040   0.8568
  18.750   1.2067   0.09716   0.09239  -0.0046   0.0038   0.8755
  19.000   1.2032   0.10183   0.09730  -0.0070   0.0036   0.9371
  19.250   1.1975   0.10650   0.10210  -0.0093   0.0035   1.0000
<< Back to EPPLER 544 AIRFOIL (e544-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 544 AIRFOIL (e544-il)