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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 100,000
Max Cl/Cd: 57.22 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae31-il-100000-n5.txt
Download as CSV file: xf-dae31-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0074   0.10522   0.09969  -0.1016   0.9118   0.0454
  -9.500   0.0135   0.10313   0.09761  -0.1027   0.9067   0.0471
  -9.250   0.0142   0.10158   0.09608  -0.1054   0.9010   0.0482
  -9.000   0.0283   0.09826   0.09276  -0.1059   0.8978   0.0490
  -8.750   0.0414   0.09560   0.09008  -0.1069   0.8949   0.0506
  -8.500   0.0471   0.09358   0.08809  -0.1075   0.8899   0.0519
  -8.250   0.0514   0.09165   0.08618  -0.1086   0.8847   0.0532
  -8.000   0.0530   0.08991   0.08445  -0.1105   0.8797   0.0539
  -7.750   0.0507   0.08839   0.08296  -0.1123   0.8741   0.0542
  -7.500   0.0665   0.08520   0.07979  -0.1110   0.8709   0.0551
  -7.250   0.0745   0.08308   0.07769  -0.1109   0.8663   0.0561
  -7.000   0.0811   0.08102   0.07562  -0.1112   0.8621   0.0573
  -6.750   0.0839   0.07922   0.07384  -0.1116   0.8576   0.0587
  -6.500   0.0784   0.07815   0.07283  -0.1116   0.8503   0.0599
  -6.250   0.0798   0.07614   0.07083  -0.1163   0.8444   0.0607
  -6.000   0.0915   0.07326   0.06794  -0.1177   0.8414   0.0612
  -5.750   0.0961   0.07157   0.06630  -0.1158   0.8355   0.0618
  -5.500   0.1044   0.06960   0.06434  -0.1158   0.8302   0.0629
  -5.250   0.1172   0.06717   0.06189  -0.1177   0.8262   0.0642
  -5.000   0.1346   0.06428   0.05895  -0.1214   0.8232   0.0658
  -4.750   0.1469   0.06123   0.05580  -0.1292   0.8141   0.0682
  -4.250   0.1840   0.05325   0.04765  -0.1326   0.8068   0.0465
  -3.750   0.2336   0.04289   0.03666  -0.1425   0.7959   0.0379
  -3.500   0.2601   0.03987   0.03337  -0.1447   0.7919   0.0374
  -3.250   0.2925   0.03628   0.02934  -0.1476   0.7891   0.0369
  -3.000   0.3265   0.03311   0.02560  -0.1499   0.7870   0.0369
  -2.750   0.3467   0.03129   0.02324  -0.1496   0.7806   0.0379
  -2.500   0.3695   0.03047   0.02230  -0.1493   0.7755   0.0397
  -2.250   0.3998   0.02901   0.02046  -0.1498   0.7724   0.0412
  -2.000   0.4322   0.02750   0.01852  -0.1504   0.7701   0.0423
  -1.750   0.4647   0.02632   0.01710  -0.1509   0.7683   0.0438
  -1.500   0.4760   0.02644   0.01720  -0.1486   0.7591   0.0456
  -1.250   0.5044   0.02576   0.01637  -0.1485   0.7555   0.0492
  -1.000   0.5351   0.02501   0.01554  -0.1487   0.7529   0.0527
  -0.750   0.5674   0.02427   0.01477  -0.1490   0.7509   0.0577
  -0.500   0.5789   0.02457   0.01509  -0.1468   0.7416   0.0624
  -0.250   0.6077   0.02408   0.01458  -0.1467   0.7379   0.0708
   0.000   0.6395   0.02350   0.01399  -0.1470   0.7353   0.0873
   0.250   0.6726   0.02280   0.01342  -0.1475   0.7333   0.1264
   0.750   0.7158   0.02234   0.01386  -0.1461   0.7199   0.4174
   1.250   0.7629   0.02144   0.01387  -0.1440   0.7088   1.0000
   1.500   0.7912   0.02141   0.01365  -0.1437   0.7041   1.0000
   1.750   0.8240   0.02116   0.01323  -0.1440   0.7012   1.0000
   2.250   0.8680   0.02163   0.01350  -0.1420   0.6875   1.0000
   2.500   0.9013   0.02134   0.01309  -0.1424   0.6843   1.0000
   2.750   0.9170   0.02184   0.01355  -0.1406   0.6752   1.0000
   3.000   0.9458   0.02172   0.01335  -0.1404   0.6700   1.0000
   3.250   0.9807   0.02133   0.01287  -0.1409   0.6666   1.0000
   3.500   0.9930   0.02195   0.01348  -0.1387   0.6561   1.0000
   3.750   1.0258   0.02163   0.01311  -0.1389   0.6514   1.0000
   4.000   1.0431   0.02201   0.01347  -0.1373   0.6421   1.0000
   4.250   1.0726   0.02183   0.01325  -0.1372   0.6358   1.0000
   4.500   1.0943   0.02201   0.01342  -0.1360   0.6273   1.0000
   4.750   1.1207   0.02197   0.01337  -0.1355   0.6195   1.0000
   5.000   1.1431   0.02212   0.01350  -0.1345   0.6107   1.0000
   5.250   1.1699   0.02207   0.01343  -0.1340   0.6022   1.0000
   5.500   1.1894   0.02232   0.01369  -0.1326   0.5920   1.0000
   5.750   1.2211   0.02210   0.01345  -0.1328   0.5835   1.0000
   6.000   1.2355   0.02253   0.01389  -0.1306   0.5717   1.0000
   6.250   1.2605   0.02258   0.01392  -0.1299   0.5613   1.0000
   6.500   1.2856   0.02264   0.01395  -0.1292   0.5502   1.0000
   6.750   1.3009   0.02308   0.01443  -0.1273   0.5377   1.0000
   7.000   1.3215   0.02335   0.01468  -0.1260   0.5255   1.0000
   7.250   1.3452   0.02351   0.01480  -0.1252   0.5135   1.0000
   7.500   1.3611   0.02399   0.01528  -0.1234   0.5002   1.0000
   7.750   1.3761   0.02454   0.01586  -0.1216   0.4868   1.0000
   8.000   1.3925   0.02506   0.01636  -0.1199   0.4735   1.0000
   8.250   1.4092   0.02557   0.01685  -0.1184   0.4601   1.0000
   8.500   1.4252   0.02614   0.01738  -0.1167   0.4463   1.0000
   8.750   1.4360   0.02696   0.01825  -0.1146   0.4320   1.0000
   9.000   1.4475   0.02779   0.01909  -0.1126   0.4177   1.0000
   9.250   1.4588   0.02865   0.01995  -0.1107   0.4035   1.0000
   9.500   1.4699   0.02956   0.02086  -0.1088   0.3894   1.0000
   9.750   1.4806   0.03052   0.02181  -0.1069   0.3755   1.0000
  10.000   1.4904   0.03156   0.02283  -0.1050   0.3616   1.0000
  10.250   1.4983   0.03276   0.02406  -0.1030   0.3475   1.0000
  10.500   1.5061   0.03400   0.02533  -0.1011   0.3338   1.0000
  10.750   1.5138   0.03529   0.02664  -0.0992   0.3206   1.0000
  11.000   1.5209   0.03665   0.02801  -0.0974   0.3078   1.0000
  11.500   1.5330   0.03965   0.03105  -0.0939   0.2825   1.0000
  11.750   1.5385   0.04127   0.03272  -0.0922   0.2705   1.0000
  12.000   1.5434   0.04296   0.03443  -0.0906   0.2592   1.0000
  12.250   1.5476   0.04476   0.03624  -0.0890   0.2481   1.0000
  12.500   1.5516   0.04665   0.03821  -0.0875   0.2369   1.0000
  12.750   1.5551   0.04863   0.04023  -0.0861   0.2267   1.0000
  13.000   1.5579   0.05072   0.04234  -0.0848   0.2169   1.0000
  13.250   1.5609   0.05292   0.04463  -0.0836   0.2069   1.0000
  13.500   1.5631   0.05521   0.04697  -0.0825   0.1979   1.0000
  13.750   1.5645   0.05765   0.04946  -0.0815   0.1889   1.0000
  14.000   1.5664   0.06015   0.05207  -0.0807   0.1803   1.0000
  14.250   1.5663   0.06287   0.05478  -0.0798   0.1725   1.0000
  14.500   1.5673   0.06563   0.05770  -0.0792   0.1641   1.0000
  14.750   1.5669   0.06856   0.06066  -0.0787   0.1569   1.0000
  15.000   1.5662   0.07165   0.06388  -0.0783   0.1493   1.0000
  15.250   1.5651   0.07483   0.06714  -0.0781   0.1425   1.0000
  15.500   1.5631   0.07822   0.07064  -0.0780   0.1358   1.0000
  15.750   1.5612   0.08168   0.07419  -0.0780   0.1294   1.0000
  16.000   1.5579   0.08539   0.07800  -0.0782   0.1233   1.0000
  16.250   1.5551   0.08913   0.08185  -0.0786   0.1175   1.0000
  16.500   1.5509   0.09313   0.08595  -0.0791   0.1119   1.0000
  16.750   1.5472   0.09713   0.09007  -0.0798   0.1066   1.0000
  17.000   1.5423   0.10138   0.09443  -0.0807   0.1015   1.0000
  17.250   1.5378   0.10564   0.09880  -0.0817   0.0967   1.0000
  17.500   1.5323   0.11014   0.10342  -0.0830   0.0920   1.0000
  17.750   1.5272   0.11463   0.10800  -0.0843   0.0876   1.0000
  18.000   1.5213   0.11933   0.11283  -0.0860   0.0832   1.0000
  18.250   1.5156   0.12400   0.11758  -0.0877   0.0792   1.0000
  18.500   1.5095   0.12887   0.12259  -0.0897   0.0752   1.0000
  18.750   1.5039   0.13364   0.12742  -0.0918   0.0717   1.0000
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