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EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 542 AIRFOIL (e542-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.69 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e542-il-1000000.txt
Download as CSV file: xf-e542-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 542 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7030   0.03892   0.03586  -0.0662   0.9932   0.0055
 -11.000  -0.6991   0.03694   0.03375  -0.0653   0.9745   0.0056
 -10.750  -0.7207   0.02637   0.02213  -0.0628   0.9561   0.0041
 -10.500  -0.6834   0.02381   0.01923  -0.0669   0.9476   0.0042
 -10.250  -0.6343   0.02222   0.01745  -0.0731   0.9401   0.0047
 -10.000  -0.5843   0.02034   0.01531  -0.0790   0.9283   0.0047
  -9.750  -0.5395   0.01969   0.01444  -0.0837   0.9054   0.0051
  -9.500  -0.5142   0.01835   0.01284  -0.0839   0.8816   0.0055
  -9.000  -0.4784   0.01725   0.01149  -0.0814   0.8456   0.0058
  -8.750  -0.4613   0.01667   0.01081  -0.0799   0.8319   0.0058
  -8.500  -0.4457   0.01600   0.01004  -0.0781   0.8196   0.0058
  -8.250  -0.4272   0.01568   0.00964  -0.0769   0.8086   0.0061
  -8.000  -0.4107   0.01518   0.00906  -0.0752   0.7977   0.0062
  -7.750  -0.3938   0.01472   0.00852  -0.0737   0.7880   0.0063
  -7.250  -0.3594   0.01389   0.00756  -0.0706   0.7699   0.0066
  -6.750  -0.3226   0.01322   0.00677  -0.0679   0.7541   0.0071
  -6.500  -0.3064   0.01281   0.00629  -0.0661   0.7465   0.0075
  -6.250  -0.2887   0.01244   0.00590  -0.0646   0.7394   0.0082
  -6.000  -0.2703   0.01215   0.00556  -0.0631   0.7323   0.0088
  -5.750  -0.2542   0.01177   0.00514  -0.0612   0.7257   0.0109
  -5.500  -0.2376   0.01142   0.00477  -0.0594   0.7192   0.0153
  -5.250  -0.2251   0.01097   0.00440  -0.0569   0.7130   0.0334
  -5.000  -0.2124   0.01054   0.00408  -0.0544   0.7074   0.0586
  -4.750  -0.2021   0.01015   0.00380  -0.0515   0.7015   0.0870
  -4.500  -0.1956   0.00987   0.00359  -0.0476   0.6956   0.1180
  -4.250  -0.1853   0.00947   0.00337  -0.0446   0.6905   0.1632
  -4.000  -0.1781   0.00892   0.00310  -0.0411   0.6851   0.2391
  -3.750  -0.1841   0.00780   0.00262  -0.0353   0.6800   0.4059
  -3.500  -0.1894   0.00623   0.00196  -0.0298   0.6757   0.6300
  -3.250  -0.1664   0.00616   0.00216  -0.0288   0.6712   0.7200
  -3.000  -0.1383   0.00630   0.00223  -0.0289   0.6667   0.7338
  -2.750  -0.1101   0.00649   0.00234  -0.0290   0.6623   0.7440
  -2.500  -0.0812   0.00667   0.00252  -0.0292   0.6584   0.7506
  -2.250  -0.0523   0.00692   0.00274  -0.0294   0.6544   0.7579
  -2.000  -0.0238   0.00721   0.00301  -0.0294   0.6504   0.7642
  -1.750   0.0055   0.00771   0.00350  -0.0294   0.6463   0.7709
  -1.500   0.0345   0.00807   0.00385  -0.0294   0.6428   0.7776
  -1.250   0.0630   0.00818   0.00396  -0.0295   0.6392   0.7796
  -1.000   0.0911   0.00818   0.00391  -0.0298   0.6355   0.7804
  -0.750   0.1191   0.00820   0.00387  -0.0301   0.6316   0.7812
  -0.500   0.1475   0.00819   0.00384  -0.0304   0.6283   0.7819
  -0.250   0.1758   0.00815   0.00379  -0.0308   0.6249   0.7826
   0.000   0.2041   0.00814   0.00375  -0.0311   0.6213   0.7835
   0.250   0.2321   0.00815   0.00371  -0.0314   0.6178   0.7843
   0.500   0.2602   0.00816   0.00368  -0.0318   0.6140   0.7850
   0.750   0.2885   0.00812   0.00363  -0.0322   0.6107   0.7857
   1.000   0.3167   0.00809   0.00359  -0.0325   0.6068   0.7864
   1.250   0.3445   0.00808   0.00355  -0.0328   0.6026   0.7872
   1.500   0.3723   0.00812   0.00354  -0.0331   0.5980   0.7881
   1.750   0.4005   0.00809   0.00352  -0.0335   0.5945   0.7888
   2.000   0.4287   0.00806   0.00350  -0.0338   0.5905   0.7894
   2.250   0.4564   0.00807   0.00348  -0.0341   0.5862   0.7900
   2.500   0.4841   0.00811   0.00348  -0.0344   0.5817   0.7906
   2.750   0.5123   0.00808   0.00348  -0.0348   0.5776   0.7911
   3.000   0.5401   0.00809   0.00348  -0.0351   0.5730   0.7916
   3.250   0.5674   0.00813   0.00349  -0.0353   0.5682   0.7920
   3.500   0.5951   0.00815   0.00353  -0.0355   0.5636   0.7925
   3.750   0.6223   0.00807   0.00347  -0.0357   0.5584   0.7935
   4.000   0.6490   0.00807   0.00347  -0.0358   0.5528   0.7942
   4.250   0.6760   0.00808   0.00349  -0.0359   0.5473   0.7947
   4.500   0.7031   0.00809   0.00352  -0.0361   0.5411   0.7953
   5.000   0.7561   0.00816   0.00362  -0.0361   0.5277   0.7964
   5.250   0.7814   0.00823   0.00368  -0.0359   0.5194   0.7970
   5.500   0.8078   0.00827   0.00375  -0.0359   0.5100   0.7976
   5.750   0.8326   0.00835   0.00383  -0.0356   0.4989   0.7982
   6.000   0.8567   0.00846   0.00392  -0.0352   0.4860   0.7988
   6.250   0.8799   0.00859   0.00403  -0.0346   0.4689   0.7995
   6.500   0.9016   0.00878   0.00416  -0.0337   0.4473   0.8002
   6.750   0.9205   0.00905   0.00434  -0.0323   0.4214   0.8009
   7.000   0.9369   0.00940   0.00458  -0.0305   0.3907   0.8019
   7.250   0.9512   0.00981   0.00486  -0.0283   0.3592   0.8029
   7.500   0.9612   0.01024   0.00515  -0.0252   0.3271   0.8039
   7.750   0.9695   0.01070   0.00548  -0.0219   0.2956   0.8048
   8.000   0.9782   0.01123   0.00587  -0.0187   0.2657   0.8057
   8.250   0.9876   0.01177   0.00629  -0.0158   0.2395   0.8065
   8.500   0.9958   0.01236   0.00675  -0.0127   0.2123   0.8072
   8.750   1.0059   0.01289   0.00721  -0.0101   0.1935   0.8079
   9.000   1.0135   0.01353   0.00774  -0.0072   0.1705   0.8084
   9.250   1.0215   0.01411   0.00825  -0.0044   0.1522   0.8097
   9.500   1.0247   0.01493   0.00895  -0.0011   0.1278   0.8109
   9.750   1.0336   0.01559   0.00958   0.0012   0.1147   0.8119
  10.000   1.0367   0.01655   0.01042   0.0042   0.0955   0.8129
  10.250   1.0426   0.01745   0.01127   0.0067   0.0809   0.8139
  10.500   1.0531   0.01820   0.01202   0.0085   0.0739   0.8150
  10.750   1.0591   0.01920   0.01298   0.0107   0.0625   0.8162
  11.000   1.0661   0.02020   0.01395   0.0126   0.0533   0.8173
  11.250   1.0755   0.02113   0.01488   0.0142   0.0470   0.8183
  11.500   1.0840   0.02214   0.01589   0.0157   0.0414   0.8193
  11.750   1.0905   0.02330   0.01703   0.0174   0.0343   0.8203
  12.000   1.0984   0.02443   0.01815   0.0187   0.0298   0.8212
  12.250   1.1058   0.02563   0.01935   0.0201   0.0255   0.8221
  12.500   1.1136   0.02684   0.02057   0.0213   0.0221   0.8229
  12.750   1.1234   0.02796   0.02172   0.0223   0.0204   0.8236
  13.000   1.1303   0.02931   0.02309   0.0234   0.0179   0.8242
  13.250   1.1389   0.03054   0.02435   0.0243   0.0159   0.8255
  13.500   1.1465   0.03188   0.02573   0.0252   0.0145   0.8268
  13.750   1.1547   0.03323   0.02713   0.0260   0.0129   0.8279
  14.000   1.1615   0.03473   0.02866   0.0267   0.0119   0.8290
  14.250   1.1694   0.03617   0.03015   0.0274   0.0102   0.8301
  14.500   1.1759   0.03778   0.03182   0.0280   0.0093   0.8312
  14.750   1.1835   0.03935   0.03344   0.0285   0.0082   0.8323
  15.000   1.1885   0.04117   0.03529   0.0289   0.0064   0.8335
  15.250   1.1934   0.04306   0.03723   0.0293   0.0056   0.8348
  15.500   1.1859   0.04617   0.04037   0.0301   0.0023   0.8359
  15.750   1.1907   0.04823   0.04249   0.0302   0.0022   0.8370
  16.000   1.1916   0.05072   0.04506   0.0304   0.0019   0.8379
  16.250   1.1940   0.05313   0.04755   0.0303   0.0018   0.8388
  16.500   1.1953   0.05575   0.05026   0.0302   0.0016   0.8396
  16.750   1.1971   0.05836   0.05296   0.0299   0.0014   0.8407
  17.000   1.1976   0.06118   0.05589   0.0295   0.0014   0.8421
  17.250   1.1984   0.06404   0.05884   0.0290   0.0013   0.8434
  17.500   1.1984   0.06707   0.06196   0.0284   0.0013   0.8447
  17.750   1.1898   0.07131   0.06634   0.0274   0.0011   0.8458
  18.000   1.1922   0.07421   0.06932   0.0265   0.0011   0.8470
  18.250   1.1896   0.07787   0.07308   0.0253   0.0011   0.8481
  18.500   1.1874   0.08158   0.07689   0.0240   0.0011   0.8493
  18.750   1.1738   0.08709   0.08255   0.0220   0.0010   0.8502
  19.000   1.1671   0.09174   0.08732   0.0201   0.0010   0.8512
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