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EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 540 AIRFOIL (e540-il)
Reynolds number: 500,000
Max Cl/Cd: 82.52 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e540-il-500000-n5.txt
Download as CSV file: xf-e540-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 540 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5478   0.07785   0.07545  -0.0722   1.0000   0.0036
 -13.000  -0.5813   0.06858   0.06601  -0.0768   1.0000   0.0036
 -12.750  -0.5975   0.06195   0.05921  -0.0810   0.9984   0.0035
 -12.500  -0.6255   0.05445   0.05143  -0.0835   0.9896   0.0034
 -12.250  -0.6486   0.04873   0.04543  -0.0838   0.9690   0.0034
 -12.000  -0.6601   0.04275   0.03903  -0.0861   0.9548   0.0034
 -11.750  -0.6546   0.03786   0.03372  -0.0893   0.9450   0.0033
 -11.500  -0.6370   0.03364   0.02905  -0.0933   0.9361   0.0033
 -11.250  -0.6111   0.03005   0.02501  -0.0973   0.9252   0.0033
 -11.000  -0.5809   0.02767   0.02228  -0.1006   0.9114   0.0033
 -10.750  -0.5557   0.02593   0.02024  -0.1021   0.8957   0.0033
 -10.500  -0.5354   0.02464   0.01871  -0.1022   0.8810   0.0034
 -10.250  -0.5174   0.02358   0.01745  -0.1015   0.8686   0.0034
  -9.750  -0.4841   0.02181   0.01537  -0.0993   0.8477   0.0036
  -9.500  -0.4679   0.02106   0.01447  -0.0981   0.8389   0.0036
  -9.250  -0.4518   0.02036   0.01365  -0.0968   0.8304   0.0037
  -9.000  -0.4364   0.01965   0.01282  -0.0954   0.8227   0.0038
  -8.750  -0.4202   0.01907   0.01214  -0.0941   0.8155   0.0038
  -8.500  -0.4045   0.01845   0.01143  -0.0926   0.8091   0.0041
  -8.250  -0.3888   0.01786   0.01076  -0.0911   0.8029   0.0042
  -8.000  -0.3717   0.01739   0.01021  -0.0899   0.7975   0.0042
  -7.750  -0.3575   0.01675   0.00951  -0.0882   0.7916   0.0046
  -7.250  -0.3239   0.01585   0.00849  -0.0855   0.7815   0.0059
  -7.000  -0.3065   0.01546   0.00804  -0.0842   0.7765   0.0063
  -6.500  -0.2730   0.01464   0.00713  -0.0813   0.7680   0.0085
  -6.250  -0.2568   0.01424   0.00672  -0.0797   0.7638   0.0120
  -6.000  -0.2413   0.01383   0.00631  -0.0780   0.7598   0.0181
  -5.750  -0.2269   0.01340   0.00591  -0.0762   0.7560   0.0296
  -5.500  -0.2147   0.01293   0.00552  -0.0740   0.7518   0.0473
  -5.250  -0.2064   0.01246   0.00516  -0.0710   0.7477   0.0740
  -5.000  -0.2004   0.01203   0.00485  -0.0675   0.7443   0.1087
  -4.750  -0.1918   0.01148   0.00452  -0.0645   0.7410   0.1613
  -4.500  -0.1850   0.01078   0.00413  -0.0614   0.7374   0.2381
  -4.250  -0.1792   0.00992   0.00367  -0.0581   0.7338   0.3416
  -4.000  -0.1793   0.00850   0.00294  -0.0541   0.7306   0.5141
  -3.750  -0.1624   0.00812   0.00310  -0.0522   0.7278   0.6510
  -3.500  -0.1347   0.00824   0.00317  -0.0523   0.7251   0.6768
  -3.250  -0.1067   0.00843   0.00332  -0.0523   0.7224   0.6920
  -3.000  -0.0786   0.00867   0.00348  -0.0524   0.7198   0.7044
  -2.750  -0.0497   0.00908   0.00389  -0.0523   0.7174   0.7134
  -2.500  -0.0214   0.00931   0.00405  -0.0525   0.7151   0.7204
  -2.250   0.0070   0.00933   0.00405  -0.0528   0.7126   0.7218
  -2.000   0.0352   0.00931   0.00398  -0.0531   0.7101   0.7228
  -1.750   0.0634   0.00929   0.00391  -0.0535   0.7075   0.7237
  -1.500   0.0917   0.00926   0.00383  -0.0538   0.7050   0.7246
  -1.250   0.1202   0.00925   0.00376  -0.0543   0.7028   0.7256
  -1.000   0.1488   0.00925   0.00370  -0.0547   0.7007   0.7267
  -0.750   0.1768   0.00921   0.00365  -0.0551   0.6981   0.7276
  -0.500   0.2050   0.00918   0.00359  -0.0555   0.6954   0.7286
  -0.250   0.2332   0.00916   0.00354  -0.0559   0.6928   0.7295
   0.000   0.2616   0.00915   0.00349  -0.0563   0.6902   0.7306
   0.250   0.2902   0.00915   0.00343  -0.0568   0.6877   0.7317
   0.500   0.3183   0.00913   0.00340  -0.0572   0.6847   0.7325
   0.750   0.3459   0.00911   0.00339  -0.0574   0.6811   0.7331
   1.000   0.3737   0.00910   0.00338  -0.0577   0.6775   0.7337
   1.250   0.4017   0.00911   0.00337  -0.0580   0.6741   0.7343
   1.500   0.4294   0.00912   0.00339  -0.0582   0.6704   0.7349
   1.750   0.4566   0.00912   0.00341  -0.0584   0.6659   0.7355
   2.000   0.4840   0.00913   0.00342  -0.0585   0.6615   0.7362
   2.250   0.5114   0.00915   0.00345  -0.0587   0.6570   0.7370
   2.500   0.5381   0.00916   0.00350  -0.0587   0.6517   0.7378
   2.750   0.5651   0.00918   0.00352  -0.0588   0.6465   0.7386
   3.000   0.5919   0.00919   0.00357  -0.0589   0.6411   0.7394
   3.250   0.6183   0.00921   0.00361  -0.0589   0.6347   0.7402
   3.500   0.6447   0.00923   0.00364  -0.0588   0.6283   0.7410
   3.750   0.6706   0.00925   0.00369  -0.0587   0.6205   0.7418
   4.000   0.6962   0.00929   0.00375  -0.0585   0.6122   0.7426
   4.250   0.7209   0.00934   0.00379  -0.0582   0.6020   0.7435
   4.500   0.7453   0.00939   0.00386  -0.0577   0.5897   0.7444
   4.750   0.7685   0.00947   0.00393  -0.0571   0.5748   0.7452
   5.000   0.7901   0.00958   0.00402  -0.0561   0.5543   0.7461
   5.250   0.8079   0.00979   0.00413  -0.0543   0.5257   0.7471
   5.500   0.8203   0.01013   0.00433  -0.0515   0.4890   0.7480
   5.750   0.8301   0.01055   0.00460  -0.0483   0.4508   0.7489
   6.000   0.8372   0.01097   0.00489  -0.0445   0.4174   0.7498
   6.250   0.8444   0.01143   0.00523  -0.0408   0.3838   0.7507
   6.500   0.8522   0.01199   0.00567  -0.0375   0.3504   0.7516
   6.750   0.8602   0.01258   0.00614  -0.0342   0.3186   0.7527
   7.000   0.8687   0.01319   0.00663  -0.0312   0.2885   0.7537
   7.250   0.8766   0.01384   0.00716  -0.0282   0.2578   0.7548
   7.500   0.8835   0.01458   0.00775  -0.0252   0.2257   0.7559
   7.750   0.8907   0.01535   0.00839  -0.0224   0.1958   0.7570
   8.000   0.8996   0.01610   0.00903  -0.0199   0.1709   0.7581
   8.250   0.9099   0.01682   0.00968  -0.0178   0.1508   0.7593
   8.500   0.9205   0.01758   0.01037  -0.0158   0.1315   0.7605
   8.750   0.9315   0.01834   0.01108  -0.0139   0.1145   0.7615
   9.000   0.9410   0.01919   0.01186  -0.0119   0.0972   0.7625
   9.250   0.9523   0.01998   0.01263  -0.0102   0.0841   0.7634
   9.500   0.9641   0.02078   0.01342  -0.0087   0.0727   0.7644
   9.750   0.9757   0.02161   0.01424  -0.0071   0.0623   0.7654
  10.000   0.9870   0.02249   0.01511  -0.0057   0.0527   0.7664
  10.250   0.9981   0.02341   0.01602  -0.0042   0.0444   0.7675
  10.500   1.0084   0.02441   0.01702  -0.0028   0.0365   0.7686
  10.750   1.0200   0.02535   0.01797  -0.0015   0.0306   0.7697
  11.000   1.0309   0.02636   0.01899  -0.0003   0.0256   0.7709
  11.250   1.0426   0.02734   0.02000   0.0008   0.0225   0.7720
  11.500   1.0525   0.02847   0.02112   0.0020   0.0184   0.7732
  11.750   1.0649   0.02945   0.02218   0.0030   0.0170   0.7743
  12.250   1.0848   0.03180   0.02460   0.0051   0.0129   0.7765
  12.500   1.0960   0.03291   0.02579   0.0060   0.0115   0.7778
  12.750   1.1060   0.03414   0.02709   0.0069   0.0103   0.7790
  13.000   1.1143   0.03554   0.02854   0.0078   0.0085   0.7803
  13.250   1.1238   0.03688   0.02996   0.0086   0.0074   0.7816
  13.500   1.1324   0.03833   0.03148   0.0094   0.0064   0.7828
  13.750   1.1398   0.03992   0.03313   0.0101   0.0057   0.7841
  14.000   1.1463   0.04165   0.03492   0.0108   0.0051   0.7854
  14.250   1.1531   0.04339   0.03677   0.0114   0.0048   0.7867
  14.500   1.1600   0.04517   0.03863   0.0119   0.0042   0.7880
  14.750   1.1647   0.04719   0.04072   0.0124   0.0036   0.7893
  15.000   1.1690   0.04930   0.04293   0.0128   0.0034   0.7905
  15.250   1.1703   0.05179   0.04553   0.0132   0.0030   0.7917
  15.500   1.1732   0.05419   0.04805   0.0134   0.0030   0.7931
  15.750   1.1755   0.05671   0.05069   0.0134   0.0030   0.7945
  16.000   1.1778   0.05934   0.05347   0.0133   0.0027   0.7959
  16.250   1.1781   0.06228   0.05653   0.0131   0.0027   0.7973
  16.500   1.1777   0.06541   0.05979   0.0127   0.0026   0.7988
  16.750   1.1768   0.06867   0.06318   0.0121   0.0025   0.8003
  17.000   1.1744   0.07228   0.06691   0.0113   0.0025   0.8019
  17.250   1.1717   0.07605   0.07081   0.0102   0.0023   0.8033
  17.500   1.1677   0.08010   0.07500   0.0090   0.0022   0.8048
  17.750   1.1628   0.08440   0.07944   0.0075   0.0022   0.8063
  18.000   1.1561   0.08912   0.08431   0.0057   0.0022   0.8078
  18.250   1.1486   0.09415   0.08948   0.0036   0.0021   0.8094
  18.500   1.1413   0.09928   0.09475   0.0013   0.0021   0.8109
  18.750   1.1317   0.10494   0.10055  -0.0014   0.0020   0.8123
  19.000   1.1209   0.11095   0.10671  -0.0045   0.0020   0.8137
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