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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 500,000
Max Cl/Cd: 98.79 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e554-il-500000-n5.txt
Download as CSV file: xf-e554-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 554 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
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.7064   0.14425   0.14106  -0.0229   1.0000   0.0051
 -18.750  -0.7226   0.13637   0.13307  -0.0269   1.0000   0.0050
 -18.500  -0.7379   0.12894   0.12552  -0.0306   1.0000   0.0050
 -18.250  -0.7550   0.12133   0.11778  -0.0344   1.0000   0.0051
 -18.000  -0.7657   0.11525   0.11161  -0.0374   1.0000   0.0050
 -17.750  -0.7762   0.10929   0.10554  -0.0403   1.0000   0.0050
 -17.500  -0.7882   0.10329   0.09943  -0.0431   1.0000   0.0050
 -17.250  -0.7976   0.09779   0.09380  -0.0458   1.0000   0.0052
 -17.000  -0.8052   0.09287   0.08881  -0.0480   1.0000   0.0050
 -16.750  -0.8113   0.08818   0.08400  -0.0502   1.0000   0.0051
 -16.500  -0.8193   0.08346   0.07919  -0.0522   1.0000   0.0051
 -16.250  -0.8230   0.07942   0.07505  -0.0539   1.0000   0.0052
 -16.000  -0.8267   0.07551   0.07104  -0.0555   1.0000   0.0052
 -15.750  -0.8301   0.07176   0.06719  -0.0569   1.0000   0.0053
 -15.500  -0.8316   0.06834   0.06369  -0.0582   1.0000   0.0052
 -15.250  -0.8333   0.06499   0.06026  -0.0593   1.0000   0.0053
 -15.000  -0.8342   0.06185   0.05705  -0.0603   1.0000   0.0054
 -14.750  -0.8365   0.05864   0.05377  -0.0612   1.0000   0.0054
 -14.500  -0.8362   0.05582   0.05088  -0.0619   1.0000   0.0054
 -14.250  -0.8376   0.05290   0.04791  -0.0626   1.0000   0.0056
 -14.000  -0.8365   0.05035   0.04530  -0.0630   1.0000   0.0056
 -13.750  -0.8354   0.04792   0.04282  -0.0634   1.0000   0.0057
 -13.500  -0.8351   0.04555   0.04039  -0.0635   1.0000   0.0058
 -13.250  -0.8329   0.04345   0.03824  -0.0635   1.0000   0.0058
 -13.000  -0.8304   0.04143   0.03617  -0.0633   1.0000   0.0059
 -12.750  -0.8285   0.03944   0.03413  -0.0630   1.0000   0.0060
 -12.500  -0.8271   0.03748   0.03212  -0.0626   1.0000   0.0061
 -12.250  -0.8244   0.03571   0.03031  -0.0620   1.0000   0.0062
 -12.000  -0.8235   0.03389   0.02845  -0.0612   1.0000   0.0063
 -11.750  -0.8225   0.03219   0.02670  -0.0602   1.0000   0.0064
 -11.500  -0.7978   0.03028   0.02473  -0.0637   0.9965   0.0067
 -11.250  -0.7815   0.02844   0.02283  -0.0654   0.9874   0.0068
 -11.000  -0.7731   0.02679   0.02113  -0.0654   0.9581   0.0069
 -10.750  -0.7253   0.02471   0.01894  -0.0733   0.9333   0.0074
 -10.250  -0.5813   0.02118   0.01502  -0.0977   0.8623   0.0092
 -10.000  -0.5692   0.02001   0.01363  -0.0977   0.8159   0.0099
  -9.750  -0.5663   0.01899   0.01244  -0.0959   0.7859   0.0103
  -9.500  -0.5603   0.01814   0.01143  -0.0943   0.7623   0.0109
  -9.250  -0.5472   0.01749   0.01065  -0.0931   0.7435   0.0118
  -9.000  -0.5322   0.01688   0.00995  -0.0920   0.7269   0.0130
  -8.750  -0.5141   0.01639   0.00935  -0.0911   0.7115   0.0143
  -8.500  -0.4953   0.01590   0.00877  -0.0903   0.6970   0.0163
  -8.250  -0.4750   0.01544   0.00824  -0.0897   0.6826   0.0193
  -8.000  -0.4535   0.01501   0.00775  -0.0892   0.6695   0.0233
  -7.750  -0.4311   0.01459   0.00728  -0.0888   0.6583   0.0282
  -7.500  -0.4083   0.01419   0.00683  -0.0884   0.6473   0.0341
  -7.250  -0.3845   0.01378   0.00641  -0.0882   0.6372   0.0423
  -7.000  -0.3606   0.01338   0.00600  -0.0880   0.6276   0.0535
  -6.750  -0.3363   0.01292   0.00558  -0.0880   0.6180   0.0712
  -6.500  -0.3120   0.01244   0.00515  -0.0879   0.6089   0.0964
  -6.250  -0.2878   0.01180   0.00466  -0.0880   0.5996   0.1379
  -6.000  -0.2643   0.01095   0.00405  -0.0882   0.5912   0.2072
  -5.750  -0.2400   0.01004   0.00350  -0.0886   0.5830   0.3011
  -5.500  -0.2129   0.00979   0.00333  -0.0888   0.5756   0.3460
  -5.250  -0.1845   0.00968   0.00323  -0.0889   0.5684   0.3667
  -5.000  -0.1563   0.00965   0.00316  -0.0890   0.5612   0.3839
  -4.750  -0.1277   0.00963   0.00310  -0.0892   0.5549   0.3980
  -4.500  -0.0991   0.00963   0.00304  -0.0893   0.5481   0.4070
  -4.250  -0.0708   0.00966   0.00301  -0.0894   0.5416   0.4173
  -4.000  -0.0418   0.00973   0.00301  -0.0895   0.5354   0.4293
  -3.750  -0.0133   0.00973   0.00299  -0.0896   0.5292   0.4349
  -3.500   0.0151   0.00974   0.00293  -0.0897   0.5239   0.4378
  -3.250   0.0441   0.00973   0.00286  -0.0899   0.5190   0.4403
  -3.000   0.0729   0.00974   0.00280  -0.0901   0.5139   0.4430
  -2.750   0.1014   0.00978   0.00274  -0.0902   0.5090   0.4455
  -2.500   0.1301   0.00976   0.00270  -0.0903   0.5046   0.4478
  -2.250   0.1588   0.00976   0.00267  -0.0905   0.4997   0.4500
  -2.000   0.1874   0.00977   0.00265  -0.0906   0.4950   0.4525
  -1.750   0.2158   0.00981   0.00263  -0.0907   0.4909   0.4552
  -1.500   0.2447   0.00983   0.00262  -0.0909   0.4874   0.4580
  -1.250   0.2735   0.00985   0.00260  -0.0911   0.4837   0.4604
  -1.000   0.3022   0.00989   0.00259  -0.0912   0.4798   0.4626
  -0.750   0.3305   0.00992   0.00260  -0.0913   0.4759   0.4648
  -0.500   0.3589   0.00995   0.00262  -0.0914   0.4724   0.4673
  -0.250   0.3877   0.00997   0.00264  -0.0916   0.4691   0.4701
   0.000   0.4164   0.01001   0.00267  -0.0918   0.4659   0.4729
   0.250   0.4449   0.01006   0.00270  -0.0919   0.4627   0.4757
   0.500   0.4732   0.01012   0.00273  -0.0920   0.4595   0.4782
   0.750   0.5013   0.01020   0.00277  -0.0921   0.4563   0.4804
   1.000   0.5300   0.01022   0.00282  -0.0923   0.4535   0.4830
   1.250   0.5586   0.01025   0.00288  -0.0924   0.4506   0.4856
   1.500   0.5869   0.01031   0.00294  -0.0926   0.4476   0.4886
   1.750   0.6151   0.01038   0.00301  -0.0926   0.4445   0.4918
   2.000   0.6431   0.01047   0.00308  -0.0927   0.4416   0.4950
   2.500   0.6996   0.01059   0.00325  -0.0929   0.4364   0.5004
   2.750   0.7278   0.01065   0.00334  -0.0930   0.4334   0.5034
   3.000   0.7558   0.01072   0.00344  -0.0931   0.4305   0.5066
   3.250   0.7837   0.01081   0.00354  -0.0932   0.4276   0.5099
   3.500   0.8112   0.01092   0.00364  -0.0932   0.4248   0.5133
   3.750   0.8388   0.01102   0.00376  -0.0932   0.4221   0.5167
   4.000   0.8669   0.01107   0.00389  -0.0933   0.4195   0.5205
   4.250   0.8947   0.01115   0.00402  -0.0933   0.4164   0.5244
   4.500   0.9223   0.01125   0.00415  -0.0933   0.4133   0.5282
   4.750   0.9494   0.01136   0.00428  -0.0933   0.4101   0.5319
   5.000   0.9761   0.01150   0.00443  -0.0932   0.4068   0.5355
   5.250   1.0037   0.01157   0.00458  -0.0932   0.4034   0.5398
   5.500   1.0309   0.01165   0.00473  -0.0932   0.3993   0.5447
   5.750   1.0576   0.01177   0.00488  -0.0930   0.3948   0.5496
   6.000   1.0835   0.01192   0.00505  -0.0928   0.3907   0.5543
   6.250   1.1105   0.01201   0.00523  -0.0927   0.3867   0.5595
   6.500   1.1371   0.01212   0.00541  -0.0926   0.3820   0.5648
   6.750   1.1627   0.01227   0.00558  -0.0923   0.3768   0.5699
   7.000   1.1883   0.01241   0.00579  -0.0920   0.3717   0.5758
   7.250   1.2141   0.01253   0.00598  -0.0917   0.3651   0.5827
   7.500   1.2383   0.01272   0.00620  -0.0912   0.3587   0.5892
   7.750   1.2637   0.01286   0.00642  -0.0909   0.3516   0.5964
   8.000   1.2870   0.01308   0.00666  -0.0903   0.3433   0.6036
   8.250   1.3109   0.01327   0.00692  -0.0897   0.3336   0.6110
   8.500   1.3328   0.01354   0.00721  -0.0889   0.3225   0.6194
   8.750   1.3534   0.01385   0.00754  -0.0878   0.3097   0.6282
   9.000   1.3723   0.01424   0.00792  -0.0865   0.2948   0.6383
   9.250   1.3892   0.01468   0.00836  -0.0848   0.2784   0.6483
   9.500   1.4027   0.01519   0.00886  -0.0826   0.2612   0.6587
   9.750   1.4126   0.01578   0.00942  -0.0798   0.2432   0.6700
  10.000   1.4204   0.01650   0.01010  -0.0768   0.2246   0.6817
  10.250   1.4255   0.01734   0.01090  -0.0735   0.2062   0.6953
  10.500   1.4301   0.01823   0.01178  -0.0704   0.1895   0.7111
  10.750   1.4337   0.01917   0.01274  -0.0672   0.1749   0.7293
  11.250   1.4375   0.02138   0.01505  -0.0613   0.1497   0.7779
  11.500   1.4372   0.02264   0.01642  -0.0585   0.1389   0.8158
  12.000   1.4315   0.02582   0.01982  -0.0533   0.1195   1.0000
  12.250   1.4296   0.02794   0.02194  -0.0517   0.1095   1.0000
  12.500   1.4293   0.03009   0.02411  -0.0505   0.1019   1.0000
  12.750   1.4258   0.03265   0.02668  -0.0495   0.0943   1.0000
  13.000   1.4235   0.03523   0.02928  -0.0487   0.0872   1.0000
  13.250   1.4214   0.03792   0.03201  -0.0481   0.0821   1.0000
  13.500   1.4182   0.04080   0.03491  -0.0477   0.0762   1.0000
  13.750   1.4142   0.04384   0.03799  -0.0474   0.0710   1.0000
  14.000   1.4099   0.04700   0.04119  -0.0472   0.0660   1.0000
  14.250   1.4072   0.05010   0.04434  -0.0472   0.0622   1.0000
  14.500   1.4034   0.05340   0.04768  -0.0474   0.0579   1.0000
  14.750   1.4003   0.05674   0.05106  -0.0476   0.0542   1.0000
  15.000   1.3972   0.06014   0.05450  -0.0480   0.0504   1.0000
  15.250   1.3942   0.06362   0.05803  -0.0485   0.0471   1.0000
  15.500   1.3928   0.06701   0.06147  -0.0491   0.0442   1.0000
  15.750   1.3891   0.07074   0.06524  -0.0498   0.0411   1.0000
  16.000   1.3879   0.07421   0.06876  -0.0506   0.0382   1.0000
  16.250   1.3850   0.07799   0.07259  -0.0515   0.0356   1.0000
  16.500   1.3838   0.08162   0.07627  -0.0525   0.0331   1.0000
  17.000   1.3802   0.08917   0.08393  -0.0546   0.0286   1.0000
  17.250   1.3779   0.09311   0.08791  -0.0559   0.0265   1.0000
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