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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 50,000
Max Cl/Cd: 33.94 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e562-il-50000-n5.txt
Download as CSV file: xf-e562-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 562 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4317   0.10047   0.09317  -0.0532   1.0000   0.0608
 -11.000  -0.4565   0.09185   0.08462  -0.0568   1.0000   0.0608
 -10.750  -0.4866   0.08313   0.07595  -0.0608   1.0000   0.0604
 -10.500  -0.5184   0.07525   0.06803  -0.0644   1.0000   0.0600
 -10.250  -0.5472   0.06891   0.06164  -0.0669   1.0000   0.0596
 -10.000  -0.5741   0.06385   0.05652  -0.0681   1.0000   0.0594
  -9.750  -0.6000   0.05993   0.05254  -0.0680   1.0000   0.0592
  -9.500  -0.6229   0.05618   0.04868  -0.0682   1.0000   0.0595
  -9.250  -0.6375   0.05260   0.04492  -0.0683   1.0000   0.0602
  -9.000  -0.6450   0.04944   0.04147  -0.0679   1.0000   0.0613
  -8.750  -0.6415   0.04747   0.03954  -0.0665   1.0000   0.0631
  -8.500  -0.6372   0.04558   0.03763  -0.0654   1.0000   0.0653
  -8.250  -0.6319   0.04352   0.03542  -0.0647   1.0000   0.0686
  -8.000  -0.6244   0.04130   0.03290  -0.0641   1.0000   0.0726
  -7.750  -0.6145   0.03982   0.03149  -0.0632   1.0000   0.0767
  -7.500  -0.6027   0.03809   0.02960  -0.0626   1.0000   0.0822
  -7.250  -0.5897   0.03650   0.02801  -0.0623   1.0000   0.0890
  -7.000  -0.5745   0.03489   0.02628  -0.0623   1.0000   0.0989
  -6.750  -0.5545   0.03330   0.02473  -0.0633   0.9989   0.1132
  -6.500  -0.5164   0.03172   0.02321  -0.0679   0.9918   0.1412
  -6.250  -0.4772   0.03082   0.02243  -0.0722   0.9843   0.1786
  -6.000  -0.4394   0.03044   0.02202  -0.0756   0.9757   0.2163
  -5.750  -0.4025   0.03038   0.02187  -0.0782   0.9668   0.2474
  -5.500  -0.3657   0.03050   0.02190  -0.0802   0.9580   0.2730
  -5.250  -0.3290   0.03050   0.02175  -0.0823   0.9489   0.2957
  -5.000  -0.2962   0.03049   0.02162  -0.0834   0.9387   0.3137
  -4.750  -0.2615   0.03036   0.02135  -0.0849   0.9292   0.3305
  -4.500  -0.2240   0.03020   0.02102  -0.0868   0.9206   0.3468
  -4.250  -0.1923   0.02998   0.02065  -0.0878   0.9097   0.3616
  -4.000  -0.1568   0.02978   0.02029  -0.0894   0.9006   0.3768
  -3.750  -0.1207   0.02950   0.01984  -0.0911   0.8913   0.3916
  -3.500  -0.0890   0.02927   0.01948  -0.0919   0.8806   0.4044
  -3.250  -0.0492   0.02896   0.01908  -0.0939   0.8734   0.4167
  -3.000  -0.0193   0.02868   0.01868  -0.0945   0.8618   0.4281
  -2.750   0.0165   0.02831   0.01813  -0.0960   0.8526   0.4412
  -2.500   0.0527   0.02796   0.01769  -0.0974   0.8439   0.4528
  -2.250   0.0840   0.02772   0.01737  -0.0979   0.8332   0.4637
  -2.000   0.1256   0.02728   0.01680  -0.1002   0.8261   0.4769
  -1.750   0.1563   0.02707   0.01648  -0.1009   0.8144   0.4893
  -1.500   0.1918   0.02681   0.01617  -0.1019   0.8054   0.5004
  -1.250   0.2268   0.02654   0.01583  -0.1030   0.7956   0.5124
  -1.000   0.2581   0.02637   0.01557  -0.1036   0.7843   0.5251
  -0.750   0.2988   0.02600   0.01510  -0.1055   0.7767   0.5386
  -0.500   0.3256   0.02596   0.01505  -0.1052   0.7643   0.5496
  -0.250   0.3567   0.02584   0.01489  -0.1056   0.7533   0.5621
   0.000   0.3946   0.02556   0.01454  -0.1070   0.7447   0.5761
   0.250   0.4219   0.02558   0.01452  -0.1069   0.7323   0.5896
   0.500   0.4513   0.02554   0.01447  -0.1069   0.7214   0.6026
   0.750   0.4861   0.02535   0.01425  -0.1077   0.7122   0.6172
   1.000   0.5109   0.02544   0.01437  -0.1071   0.7000   0.6311
   1.250   0.5392   0.02546   0.01439  -0.1070   0.6893   0.6464
   1.500   0.5716   0.02535   0.01428  -0.1074   0.6799   0.6631
   1.750   0.5946   0.02552   0.01449  -0.1065   0.6680   0.6797
   2.000   0.6217   0.02557   0.01457  -0.1061   0.6580   0.6983
   2.250   0.6500   0.02557   0.01461  -0.1058   0.6482   0.7192
   2.500   0.6704   0.02575   0.01490  -0.1044   0.6373   0.7406
   2.750   0.6977   0.02570   0.01489  -0.1038   0.6286   0.7669
   3.000   0.7159   0.02585   0.01518  -0.1018   0.6180   0.7969
   3.250   0.7353   0.02590   0.01536  -0.0999   0.6087   0.8378
   3.500   0.7621   0.02577   0.01533  -0.0992   0.5996   0.9164
   3.750   0.7921   0.02616   0.01571  -0.1004   0.5887   1.0000
   4.000   0.8284   0.02642   0.01583  -0.1021   0.5804   1.0000
   4.250   0.8526   0.02701   0.01640  -0.1021   0.5698   1.0000
   4.500   0.8806   0.02748   0.01684  -0.1024   0.5606   1.0000
   4.750   0.9091   0.02791   0.01723  -0.1027   0.5516   1.0000
   5.000   0.9318   0.02855   0.01787  -0.1023   0.5420   1.0000
   5.250   0.9629   0.02888   0.01817  -0.1028   0.5340   1.0000
   5.500   0.9815   0.02966   0.01902  -0.1017   0.5240   1.0000
   5.750   1.0148   0.02990   0.01921  -0.1024   0.5166   1.0000
   6.000   1.0294   0.03084   0.02028  -0.1009   0.5065   1.0000
   6.250   1.0584   0.03124   0.02066  -0.1010   0.4988   1.0000
   6.500   1.0754   0.03210   0.02163  -0.0997   0.4893   1.0000
   6.750   1.1004   0.03266   0.02222  -0.0993   0.4813   1.0000
   7.000   1.1194   0.03343   0.02310  -0.0982   0.4723   1.0000
   7.250   1.1402   0.03417   0.02391  -0.0973   0.4640   1.0000
   7.500   1.1611   0.03485   0.02468  -0.0964   0.4554   1.0000
   7.750   1.1774   0.03577   0.02573  -0.0950   0.4468   1.0000
   8.000   1.2008   0.03633   0.02636  -0.0943   0.4385   1.0000
   8.250   1.2113   0.03748   0.02765  -0.0922   0.4295   1.0000
   8.500   1.2386   0.03784   0.02806  -0.0920   0.4215   1.0000
   8.750   1.2416   0.03929   0.02971  -0.0891   0.4121   1.0000
   9.000   1.2756   0.03928   0.02972  -0.0894   0.4042   1.0000
   9.250   1.2666   0.04118   0.03183  -0.0852   0.3947   1.0000
   9.500   1.2903   0.04156   0.03228  -0.0844   0.3863   1.0000
   9.750   1.2891   0.04313   0.03402  -0.0812   0.3771   1.0000
  10.000   1.2989   0.04419   0.03520  -0.0792   0.3683   1.0000
  10.250   1.3117   0.04503   0.03615  -0.0774   0.3591   1.0000
  10.500   1.3030   0.04725   0.03853  -0.0742   0.3501   1.0000
  10.750   1.3350   0.04683   0.03813  -0.0738   0.3408   1.0000
  11.000   1.3052   0.05071   0.04225  -0.0699   0.3318   1.0000
  11.250   1.3186   0.05153   0.04315  -0.0684   0.3226   1.0000
  11.500   1.3125   0.05399   0.04575  -0.0665   0.3131   1.0000
  11.750   1.2963   0.05768   0.04959  -0.0648   0.3039   1.0000
  12.000   1.3260   0.05682   0.04877  -0.0637   0.2941   1.0000
  12.250   1.2802   0.06418   0.05635  -0.0630   0.2848   1.0000
  12.500   1.2826   0.06640   0.05866  -0.0623   0.2753   1.0000
  12.750   1.2954   0.06727   0.05961  -0.0613   0.2653   1.0000
  13.000   1.2451   0.07706   0.06956  -0.0632   0.2554   1.0000
  13.250   1.2610   0.07749   0.07007  -0.0622   0.2459   1.0000
  13.500   1.2602   0.08049   0.07316  -0.0623   0.2360   1.0000
  13.750   1.2132   0.09135   0.08415  -0.0659   0.2256   1.0000
  14.000   1.2401   0.08980   0.08266  -0.0641   0.2167   1.0000
  14.250   1.2297   0.09478   0.08774  -0.0654   0.2069   1.0000
  14.500   1.1886   0.10586   0.09892  -0.0699   0.1968   1.0000
  14.750   1.2326   0.10075   0.09386  -0.0663   0.1884   1.0000
  15.000   1.1939   0.11176   0.10498  -0.0711   0.1792   1.0000
  15.250   1.1758   0.11914   0.11242  -0.0743   0.1703   1.0000
  15.500   1.2303   0.11135   0.10466  -0.0691   0.1618   1.0000
  15.750   1.1548   0.13134   0.12474  -0.0796   0.1535   1.0000
  16.000   1.2058   0.12364   0.11709  -0.0744   0.1461   1.0000
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