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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 50,000
Max Cl/Cd: 40.97 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae51-il-50000-n5.txt
Download as CSV file: xf-dae51-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-51 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3345   0.10032   0.09367  -0.0346   1.0000   0.1176
  -7.750  -0.3386   0.09820   0.09167  -0.0342   1.0000   0.1198
  -7.500  -0.3517   0.09692   0.09054  -0.0328   1.0000   0.1222
  -7.250  -0.3824   0.09723   0.09109  -0.0346   1.0000   0.1251
  -7.000  -0.3926   0.09510   0.08907  -0.0352   1.0000   0.1257
  -6.750  -0.3903   0.09177   0.08578  -0.0320   1.0000   0.1266
  -6.250  -0.3878   0.08104   0.07498  -0.0358   1.0000   0.0654
  -5.750  -0.3722   0.07010   0.06381  -0.0465   0.9978   0.0544
  -5.500  -0.3473   0.06556   0.05916  -0.0507   0.9920   0.0531
  -5.250  -0.3167   0.06011   0.05348  -0.0575   0.9858   0.0523
  -5.000  -0.2834   0.05455   0.04757  -0.0646   0.9795   0.0525
  -4.750  -0.2465   0.04923   0.04174  -0.0713   0.9738   0.0531
  -4.500  -0.2096   0.04463   0.03659  -0.0765   0.9686   0.0531
  -4.250  -0.1737   0.04073   0.03213  -0.0805   0.9629   0.0530
  -4.000  -0.1337   0.03725   0.02797  -0.0844   0.9585   0.0534
  -3.750  -0.0970   0.03457   0.02461  -0.0869   0.9531   0.0554
  -3.500  -0.0633   0.03275   0.02264  -0.0891   0.9474   0.0595
  -3.250  -0.0234   0.03085   0.02028  -0.0917   0.9432   0.0629
  -3.000   0.0093   0.02938   0.01837  -0.0926   0.9368   0.0665
  -2.750   0.0444   0.02819   0.01706  -0.0942   0.9313   0.0741
  -2.500   0.0825   0.02709   0.01567  -0.0959   0.9268   0.0827
  -2.250   0.1128   0.02635   0.01483  -0.0965   0.9193   0.0971
  -2.000   0.1525   0.02543   0.01387  -0.0989   0.9145   0.1249
  -1.750   0.1868   0.02433   0.01322  -0.1008   0.9081   0.2022
  -1.500   0.2183   0.02275   0.01312  -0.1019   0.9024   0.5304
  -1.250   0.2380   0.02162   0.01291  -0.0982   0.8949   1.0000
  -1.000   0.2704   0.02184   0.01268  -0.0993   0.8867   1.0000
  -0.750   0.3026   0.02208   0.01255  -0.1003   0.8790   1.0000
  -0.500   0.3347   0.02231   0.01246  -0.1012   0.8710   1.0000
  -0.250   0.3640   0.02258   0.01248  -0.1017   0.8624   1.0000
   0.000   0.3972   0.02277   0.01245  -0.1027   0.8550   1.0000
   0.250   0.4239   0.02309   0.01258  -0.1027   0.8454   1.0000
   0.500   0.4583   0.02323   0.01254  -0.1037   0.8388   1.0000
   0.750   0.4829   0.02358   0.01277  -0.1033   0.8283   1.0000
   1.000   0.5131   0.02380   0.01287  -0.1037   0.8202   1.0000
   1.250   0.5416   0.02404   0.01302  -0.1038   0.8112   1.0000
   1.500   0.5674   0.02436   0.01328  -0.1035   0.8011   1.0000
   1.750   0.6001   0.02443   0.01329  -0.1040   0.7941   1.0000
   2.000   0.6237   0.02481   0.01364  -0.1033   0.7828   1.0000
   2.250   0.6501   0.02509   0.01389  -0.1030   0.7728   1.0000
   2.500   0.6812   0.02514   0.01395  -0.1031   0.7649   1.0000
   2.750   0.7048   0.02551   0.01432  -0.1024   0.7533   1.0000
   3.000   0.7305   0.02577   0.01461  -0.1019   0.7426   1.0000
   3.250   0.7622   0.02570   0.01456  -0.1019   0.7347   1.0000
   3.500   0.7857   0.02604   0.01498  -0.1011   0.7224   1.0000
   3.750   0.8101   0.02632   0.01532  -0.1003   0.7104   1.0000
   4.000   0.8360   0.02650   0.01557  -0.0997   0.6988   1.0000
   4.250   0.8642   0.02651   0.01569  -0.0991   0.6882   1.0000
   4.500   0.8919   0.02652   0.01579  -0.0984   0.6768   1.0000
   4.750   0.9164   0.02671   0.01609  -0.0975   0.6633   1.0000
   5.000   0.9413   0.02686   0.01636  -0.0966   0.6495   1.0000
   5.250   0.9666   0.02696   0.01662  -0.0956   0.6353   1.0000
   5.500   0.9920   0.02704   0.01682  -0.0946   0.6206   1.0000
   5.750   1.0177   0.02708   0.01699  -0.0936   0.6052   1.0000
   6.000   1.0437   0.02707   0.01711  -0.0925   0.5890   1.0000
   6.250   1.0664   0.02729   0.01750  -0.0912   0.5703   1.0000
   6.500   1.0891   0.02749   0.01784  -0.0898   0.5503   1.0000
   6.750   1.1141   0.02750   0.01795  -0.0884   0.5298   1.0000
   7.000   1.1336   0.02788   0.01848  -0.0867   0.5054   1.0000
   7.250   1.1536   0.02819   0.01891  -0.0849   0.4793   1.0000
   7.500   1.1717   0.02860   0.01938  -0.0829   0.4500   1.0000
   7.750   1.1874   0.02914   0.01994  -0.0807   0.4173   1.0000
   8.000   1.2005   0.02984   0.02059  -0.0783   0.3817   1.0000
   8.250   1.2099   0.03082   0.02155  -0.0756   0.3432   1.0000
   8.500   1.2168   0.03205   0.02266  -0.0729   0.3042   1.0000
   8.750   1.2203   0.03353   0.02397  -0.0700   0.2668   1.0000
   9.000   1.2212   0.03526   0.02558  -0.0671   0.2305   1.0000
   9.250   1.2206   0.03734   0.02748  -0.0644   0.1972   1.0000
   9.500   1.2193   0.03968   0.02965  -0.0621   0.1681   1.0000
   9.750   1.2184   0.04217   0.03205  -0.0601   0.1432   1.0000
  10.000   1.2175   0.04481   0.03458  -0.0582   0.1242   1.0000
  10.250   1.2177   0.04746   0.03724  -0.0566   0.1091   1.0000
  10.500   1.2183   0.05015   0.03991  -0.0550   0.0974   1.0000
  10.750   1.2193   0.05285   0.04259  -0.0536   0.0885   1.0000
  11.000   1.2238   0.05537   0.04525  -0.0522   0.0799   1.0000
  11.250   1.2281   0.05792   0.04783  -0.0509   0.0740   1.0000
  11.500   1.2368   0.06024   0.05038  -0.0494   0.0683   1.0000
  11.750   1.2434   0.06267   0.05272  -0.0481   0.0637   1.0000
  12.000   1.2515   0.06530   0.05575  -0.0469   0.0591   1.0000
  12.250   1.2598   0.06792   0.05860  -0.0457   0.0559   1.0000
  12.500   1.2703   0.07042   0.06112  -0.0445   0.0532   1.0000
  12.750   1.2729   0.07395   0.06497  -0.0437   0.0512   1.0000
  13.000   1.2687   0.07802   0.06942  -0.0434   0.0493   1.0000
  13.250   1.2620   0.08237   0.07408  -0.0434   0.0478   1.0000
  13.500   1.2534   0.08700   0.07898  -0.0439   0.0466   1.0000
  13.750   1.2432   0.09199   0.08421  -0.0449   0.0457   1.0000
  14.000   1.2304   0.09755   0.09002  -0.0464   0.0452   1.0000
  14.250   1.2141   0.10390   0.09662  -0.0487   0.0450   1.0000
  14.500   1.1936   0.11143   0.10440  -0.0524   0.0451   1.0000
  14.750   1.1674   0.12090   0.11412  -0.0579   0.0455   1.0000
  15.000   1.1322   0.13402   0.12748  -0.0665   0.0468   1.0000
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