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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 200,000
Max Cl/Cd: 90.85 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae31-il-200000-n5.txt
Download as CSV file: xf-dae31-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-31 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0327   0.09114   0.08672  -0.1007   0.8420   0.0281
  -8.500   0.0395   0.08874   0.08433  -0.1018   0.8387   0.0288
  -8.250   0.0453   0.08633   0.08195  -0.1030   0.8350   0.0293
  -8.000   0.0482   0.08391   0.07955  -0.1046   0.8311   0.0297
  -7.750   0.0489   0.08139   0.07705  -0.1064   0.8273   0.0298
  -7.500   0.0628   0.07892   0.07457  -0.1059   0.8249   0.0303
  -7.250   0.0716   0.07676   0.07239  -0.1063   0.8223   0.0307
  -7.000   0.0789   0.07478   0.07046  -0.1068   0.8184   0.0320
  -6.750   0.0762   0.07262   0.06836  -0.1081   0.8135   0.0335
  -6.500   0.0763   0.06971   0.06546  -0.1122   0.8090   0.0338
  -6.250   0.0903   0.06774   0.06348  -0.1108   0.8067   0.0343
  -6.000   0.1019   0.06544   0.06116  -0.1120   0.8042   0.0348
  -5.750   0.1129   0.06307   0.05882  -0.1141   0.7999   0.0354
  -5.500   0.1258   0.06039   0.05615  -0.1169   0.7957   0.0360
  -5.000   0.1619   0.04986   0.04545  -0.1300   0.7885   0.0265
  -4.500   0.2161   0.03629   0.03138  -0.1448   0.7815   0.0227
  -4.250   0.2452   0.02911   0.02358  -0.1503   0.7777   0.0228
  -4.000   0.2698   0.02927   0.02380  -0.1503   0.7745   0.0235
  -3.750   0.2983   0.02636   0.02049  -0.1521   0.7717   0.0246
  -3.500   0.3278   0.02298   0.01648  -0.1536   0.7694   0.0248
  -3.250   0.3561   0.02086   0.01386  -0.1542   0.7665   0.0251
  -3.000   0.3830   0.01943   0.01205  -0.1543   0.7621   0.0256
  -2.750   0.4106   0.01833   0.01063  -0.1542   0.7585   0.0262
  -2.500   0.4383   0.01767   0.00989  -0.1542   0.7553   0.0270
  -2.250   0.4666   0.01709   0.00918  -0.1542   0.7526   0.0286
  -2.000   0.4951   0.01651   0.00847  -0.1542   0.7501   0.0305
  -1.750   0.5207   0.01618   0.00814  -0.1539   0.7451   0.0319
  -1.500   0.5478   0.01573   0.00762  -0.1537   0.7410   0.0335
  -1.250   0.5758   0.01532   0.00721  -0.1536   0.7375   0.0354
  -1.000   0.6044   0.01497   0.00680  -0.1536   0.7346   0.0390
  -0.750   0.6314   0.01474   0.00657  -0.1534   0.7303   0.0432
  -0.500   0.6579   0.01454   0.00639  -0.1532   0.7252   0.0485
  -0.250   0.6858   0.01428   0.00614  -0.1531   0.7210   0.0585
   0.000   0.7145   0.01397   0.00586  -0.1531   0.7175   0.0775
   0.250   0.7410   0.01376   0.00582  -0.1529   0.7125   0.1224
   0.750   0.7944   0.01309   0.00580  -0.1528   0.7024   0.3548
   1.000   0.8210   0.01270   0.00579  -0.1525   0.6981   0.5122
   1.500   0.8754   0.01189   0.00574  -0.1518   0.6862   1.0000
   1.750   0.9034   0.01192   0.00564  -0.1516   0.6810   1.0000
   2.000   0.9289   0.01205   0.00572  -0.1512   0.6736   1.0000
   2.250   0.9568   0.01206   0.00562  -0.1510   0.6677   1.0000
   2.500   0.9825   0.01218   0.00570  -0.1506   0.6601   1.0000
   2.750   1.0093   0.01224   0.00568  -0.1503   0.6526   1.0000
   3.000   1.0353   0.01234   0.00572  -0.1498   0.6447   1.0000
   3.250   1.0613   0.01244   0.00575  -0.1494   0.6362   1.0000
   3.500   1.0869   0.01256   0.00583  -0.1490   0.6275   1.0000
   3.750   1.1127   0.01267   0.00588  -0.1485   0.6183   1.0000
   4.000   1.1373   0.01283   0.00601  -0.1479   0.6085   1.0000
   4.250   1.1628   0.01297   0.00607  -0.1474   0.5987   1.0000
   4.500   1.1864   0.01316   0.00624  -0.1466   0.5871   1.0000
   4.750   1.2102   0.01336   0.00639  -0.1459   0.5756   1.0000
   5.000   1.2337   0.01358   0.00653  -0.1451   0.5638   1.0000
   5.250   1.2563   0.01383   0.00675  -0.1442   0.5509   1.0000
   5.500   1.2780   0.01412   0.00699  -0.1431   0.5378   1.0000
   5.750   1.2993   0.01442   0.00724  -0.1420   0.5248   1.0000
   6.000   1.3197   0.01476   0.00751  -0.1408   0.5116   1.0000
   6.500   1.3574   0.01551   0.00819  -0.1378   0.4841   1.0000
   6.750   1.3748   0.01593   0.00857  -0.1361   0.4704   1.0000
   7.000   1.3903   0.01637   0.00898  -0.1341   0.4569   1.0000
   7.250   1.4032   0.01687   0.00942  -0.1317   0.4432   1.0000
   7.750   1.4267   0.01801   0.01050  -0.1268   0.4150   1.0000
   8.000   1.4382   0.01866   0.01113  -0.1244   0.4008   1.0000
   8.250   1.4491   0.01938   0.01181  -0.1221   0.3868   1.0000
   8.500   1.4595   0.02016   0.01257  -0.1198   0.3729   1.0000
   8.750   1.4694   0.02100   0.01338  -0.1176   0.3592   1.0000
   9.000   1.4793   0.02189   0.01424  -0.1154   0.3457   1.0000
   9.250   1.4893   0.02281   0.01515  -0.1134   0.3316   1.0000
   9.500   1.4990   0.02379   0.01612  -0.1114   0.3182   1.0000
   9.750   1.5082   0.02484   0.01715  -0.1094   0.3052   1.0000
  10.000   1.5164   0.02598   0.01827  -0.1073   0.2922   1.0000
  10.250   1.5242   0.02718   0.01944  -0.1054   0.2797   1.0000
  10.500   1.5332   0.02835   0.02063  -0.1036   0.2671   1.0000
  10.750   1.5410   0.02962   0.02190  -0.1018   0.2550   1.0000
  11.000   1.5483   0.03098   0.02325  -0.1000   0.2437   1.0000
  11.250   1.5543   0.03245   0.02472  -0.0981   0.2323   1.0000
  11.500   1.5623   0.03383   0.02612  -0.0966   0.2210   1.0000
  11.750   1.5686   0.03537   0.02768  -0.0950   0.2105   1.0000
  12.000   1.5735   0.03706   0.02937  -0.0933   0.2005   1.0000
  12.250   1.5800   0.03869   0.03102  -0.0919   0.1902   1.0000
  12.500   1.5857   0.04043   0.03279  -0.0905   0.1808   1.0000
  12.750   1.5896   0.04238   0.03475  -0.0891   0.1718   1.0000
  13.000   1.5952   0.04425   0.03666  -0.0879   0.1625   1.0000
  13.250   1.5999   0.04623   0.03868  -0.0868   0.1541   1.0000
  13.500   1.6024   0.04850   0.04096  -0.0856   0.1460   1.0000
  13.750   1.6079   0.05053   0.04306  -0.0847   0.1382   1.0000
  14.000   1.6108   0.05288   0.04545  -0.0838   0.1313   1.0000
  14.250   1.6145   0.05521   0.04784  -0.0830   0.1243   1.0000
  14.500   1.6174   0.05767   0.05037  -0.0823   0.1180   1.0000
  14.750   1.6193   0.06032   0.05307  -0.0817   0.1118   1.0000
  15.000   1.6218   0.06295   0.05578  -0.0811   0.1059   1.0000
  15.250   1.6218   0.06594   0.05881  -0.0807   0.1003   1.0000
  15.500   1.6238   0.06875   0.06172  -0.0804   0.0945   1.0000
  15.750   1.6222   0.07208   0.06510  -0.0803   0.0890   1.0000
  16.000   1.6219   0.07533   0.06842  -0.0802   0.0830   1.0000
  16.250   1.6209   0.07872   0.07190  -0.0803   0.0776   1.0000
  16.500   1.6174   0.08254   0.07577  -0.0806   0.0724   1.0000
  16.750   1.6158   0.08615   0.07946  -0.0809   0.0673   1.0000
  17.000   1.6127   0.09006   0.08345  -0.0814   0.0628   1.0000
  17.250   1.6080   0.09426   0.08772  -0.0821   0.0587   1.0000
  17.500   1.6053   0.09822   0.09180  -0.0829   0.0548   1.0000
  17.750   1.6000   0.10265   0.09631  -0.0839   0.0516   1.0000
  18.000   1.5959   0.10694   0.10071  -0.0850   0.0484   1.0000
  18.250   1.5900   0.11158   0.10545  -0.0864   0.0457   1.0000
  18.500   1.5851   0.11612   0.11010  -0.0878   0.0430   1.0000
  18.750   1.5786   0.12099   0.11506  -0.0896   0.0408   1.0000
  19.000   1.5737   0.12561   0.11980  -0.0913   0.0385   1.0000
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