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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 50,000
Max Cl/Cd: 18.05 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e554-il-50000-n5.txt
Download as CSV file: xf-e554-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5009   0.10200   0.09443  -0.0561   1.0000   0.0439
 -13.250  -0.5203   0.09472   0.08706  -0.0599   1.0000   0.0436
 -13.000  -0.5400   0.08809   0.08032  -0.0632   1.0000   0.0433
 -12.750  -0.5606   0.08184   0.07391  -0.0662   1.0000   0.0432
 -12.500  -0.5785   0.07637   0.06827  -0.0685   1.0000   0.0433
 -12.250  -0.5915   0.07181   0.06352  -0.0701   1.0000   0.0435
 -12.000  -0.6034   0.06751   0.05899  -0.0711   1.0000   0.0439
 -11.750  -0.6016   0.06465   0.05606  -0.0709   1.0000   0.0448
 -11.500  -0.5972   0.06230   0.05367  -0.0705   1.0000   0.0461
 -11.250  -0.5944   0.05986   0.05113  -0.0701   1.0000   0.0477
 -11.000  -0.5913   0.05739   0.04844  -0.0694   1.0000   0.0498
 -10.750  -0.5818   0.05559   0.04660  -0.0682   1.0000   0.0524
 -10.500  -0.5704   0.05408   0.04504  -0.0668   1.0000   0.0554
 -10.250  -0.5597   0.05253   0.04335  -0.0652   1.0000   0.0592
 -10.000  -0.5513   0.05123   0.04216  -0.0636   1.0000   0.0631
  -9.750  -0.5427   0.04993   0.04078  -0.0617   1.0000   0.0681
  -9.500  -0.5391   0.04861   0.03960  -0.0599   1.0000   0.0730
  -9.250  -0.5358   0.04736   0.03838  -0.0576   1.0000   0.0789
  -9.000  -0.5386   0.04604   0.03720  -0.0552   1.0000   0.0846
  -8.750  -0.5444   0.04487   0.03611  -0.0522   1.0000   0.0904
  -8.500  -0.5589   0.04384   0.03525  -0.0485   1.0000   0.0942
  -8.250  -0.5727   0.04285   0.03432  -0.0452   0.9972   0.0996
  -8.000  -0.5538   0.04005   0.03172  -0.0494   0.9749   0.1175
  -7.750  -0.5402   0.03676   0.02865  -0.0537   0.9516   0.1443
  -7.500  -0.5285   0.03327   0.02561  -0.0579   0.9307   0.1899
  -7.250  -0.5007   0.03346   0.02702  -0.0575   0.9151   0.3081
  -7.000  -0.4673   0.03329   0.02650  -0.0606   0.8992   0.3797
  -6.750  -0.4255   0.03492   0.02784  -0.0614   0.8855   0.4158
  -6.500  -0.3817   0.03663   0.02924  -0.0616   0.8733   0.4406
  -6.250  -0.3470   0.03689   0.02917  -0.0629   0.8598   0.4630
  -6.000  -0.3049   0.03863   0.03069  -0.0615   0.8462   0.4753
  -5.750  -0.2695   0.03915   0.03097  -0.0612   0.8326   0.4874
  -5.500  -0.2428   0.03860   0.03014  -0.0620   0.8191   0.5003
  -5.250  -0.2089   0.03862   0.02990  -0.0621   0.8068   0.5083
  -5.000  -0.1899   0.03776   0.02881  -0.0623   0.7925   0.5178
  -4.500  -0.1433   0.03633   0.02688  -0.0631   0.7689   0.5336
  -4.250  -0.1179   0.03624   0.02664  -0.0621   0.7569   0.5374
  -4.000  -0.0948   0.03579   0.02601  -0.0619   0.7461   0.5428
  -3.750  -0.0742   0.03466   0.02461  -0.0632   0.7363   0.5511
  -3.500  -0.0511   0.03452   0.02437  -0.0624   0.7258   0.5544
  -3.250  -0.0235   0.03414   0.02380  -0.0626   0.7176   0.5587
  -3.000  -0.0036   0.03362   0.02312  -0.0628   0.7075   0.5646
  -2.750   0.0232   0.03297   0.02226  -0.0639   0.7001   0.5700
  -2.500   0.0448   0.03286   0.02209  -0.0632   0.6909   0.5733
  -2.250   0.0715   0.03256   0.02164  -0.0635   0.6839   0.5776
  -2.000   0.0947   0.03220   0.02114  -0.0640   0.6758   0.5832
  -1.750   0.1203   0.03185   0.02065  -0.0647   0.6684   0.5878
  -1.500   0.1474   0.03171   0.02039  -0.0647   0.6625   0.5912
  -1.250   0.1686   0.03169   0.02036  -0.0643   0.6547   0.5954
  -1.000   0.1967   0.03144   0.01995  -0.0652   0.6489   0.6007
  -0.750   0.2219   0.03131   0.01973  -0.0658   0.6425   0.6054
  -0.500   0.2441   0.03138   0.01979  -0.0653   0.6357   0.6087
  -0.250   0.2720   0.03129   0.01961  -0.0656   0.6306   0.6130
   0.000   0.2958   0.03136   0.01963  -0.0659   0.6247   0.6184
   0.250   0.3192   0.03147   0.01971  -0.0661   0.6185   0.6232
   0.500   0.3456   0.03150   0.01971  -0.0660   0.6138   0.6270
   0.750   0.3700   0.03164   0.01982  -0.0660   0.6087   0.6316
   1.000   0.3908   0.03195   0.02013  -0.0660   0.6022   0.6371
   1.250   0.4169   0.03208   0.02024  -0.0662   0.5976   0.6419
   1.500   0.4456   0.03213   0.02025  -0.0664   0.5941   0.6466
   1.750   0.4604   0.03279   0.02100  -0.0656   0.5873   0.6519
   2.000   0.4850   0.03310   0.02130  -0.0660   0.5821   0.6577
   2.250   0.5118   0.03325   0.02146  -0.0658   0.5783   0.6623
   2.500   0.5326   0.03376   0.02201  -0.0655   0.5736   0.6681
   2.750   0.5490   0.03456   0.02287  -0.0651   0.5673   0.6747
   3.000   0.5720   0.03490   0.02325  -0.0646   0.5630   0.6797
   3.250   0.6024   0.03501   0.02337  -0.0651   0.5597   0.6863
   3.500   0.6096   0.03633   0.02481  -0.0638   0.5529   0.6927
   3.750   0.6257   0.03707   0.02565  -0.0627   0.5477   0.6986
   4.000   0.6541   0.03733   0.02594  -0.0632   0.5440   0.7065
   4.250   0.6715   0.03810   0.02680  -0.0624   0.5393   0.7134
   4.500   0.6711   0.03984   0.02868  -0.0602   0.5319   0.7204
   4.750   0.6961   0.04027   0.02917  -0.0602   0.5279   0.7289
   5.000   0.7274   0.04029   0.02926  -0.0605   0.5250   0.7379
   5.500   0.7260   0.04395   0.03320  -0.0564   0.5109   0.7557
   5.750   0.7582   0.04387   0.03321  -0.0566   0.5081   0.7669
   6.000   0.7161   0.04825   0.03772  -0.0521   0.4961   0.7763
   6.250   0.7426   0.04834   0.03795  -0.0516   0.4928   0.7898
   6.500   0.7771   0.04791   0.03764  -0.0515   0.4905   0.8057
   7.000   0.7605   0.05297   0.04301  -0.0476   0.4743   0.8429
   7.500   0.7549   0.05775   0.04816  -0.0459   0.4578   1.0000
   8.000   0.7715   0.06284   0.05328  -0.0479   0.4417   1.0000
   8.500   0.7875   0.06762   0.05813  -0.0490   0.4258   1.0000
   8.750   0.8248   0.06719   0.05774  -0.0492   0.4231   1.0000
   9.250   0.8389   0.07183   0.06247  -0.0496   0.4069   1.0000
   9.500   0.8208   0.07665   0.06735  -0.0502   0.3940   1.0000
   9.750   0.8546   0.07623   0.06700  -0.0499   0.3907   1.0000
  10.000   0.8382   0.08101   0.07183  -0.0505   0.3780   1.0000
  10.250   0.8719   0.08043   0.07134  -0.0501   0.3745   1.0000
  10.500   0.8561   0.08527   0.07624  -0.0509   0.3619   1.0000
  10.750   0.8907   0.08440   0.07548  -0.0502   0.3584   1.0000
  11.000   0.8752   0.08934   0.08048  -0.0512   0.3456   1.0000
  11.500   0.8957   0.09318   0.08450  -0.0514   0.3294   1.0000
  11.750   0.8891   0.09729   0.08868  -0.0524   0.3183   1.0000
  12.000   0.9168   0.09683   0.08835  -0.0517   0.3131   1.0000
  12.250   0.9072   0.10150   0.09309  -0.0529   0.3014   1.0000
  12.500   0.9385   0.10033   0.09205  -0.0518   0.2970   1.0000
  12.750   0.9269   0.10540   0.09719  -0.0533   0.2847   1.0000
  13.250   0.9472   0.10914   0.10115  -0.0538   0.2683   1.0000
  13.750   0.9682   0.11268   0.10491  -0.0542   0.2521   1.0000
  14.250   0.9900   0.11596   0.10842  -0.0546   0.2362   1.0000
  14.500   0.9756   0.12235   0.11486  -0.0572   0.2241   1.0000
  14.750   1.0074   0.11993   0.11258  -0.0554   0.2198   1.0000
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