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EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 544 AIRFOIL (e544-il)
Reynolds number: 500,000
Max Cl/Cd: 91.04 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e544-il-500000.txt
Download as CSV file: xf-e544-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 544 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5900   0.02243   0.01810  -0.0814   0.9518   0.0107
 -10.250  -0.5646   0.01779   0.01309  -0.0836   0.9450   0.0092
 -10.000  -0.6130   0.02699   0.02141  -0.0774   0.9477   0.0080
  -9.750  -0.5709   0.02509   0.01926  -0.0812   0.9426   0.0079
  -9.500  -0.5272   0.02332   0.01730  -0.0846   0.9352   0.0079
  -9.250  -0.4821   0.02173   0.01559  -0.0884   0.9270   0.0081
  -9.000  -0.4428   0.02058   0.01435  -0.0917   0.9121   0.0084
  -8.750  -0.4135   0.01972   0.01336  -0.0931   0.8945   0.0087
  -8.500  -0.3936   0.01906   0.01258  -0.0926   0.8772   0.0092
  -8.000  -0.3642   0.01778   0.01106  -0.0894   0.8484   0.0103
  -7.750  -0.3541   0.01703   0.01026  -0.0872   0.8359   0.0111
  -7.500  -0.3401   0.01650   0.00965  -0.0855   0.8253   0.0121
  -7.250  -0.3268   0.01597   0.00902  -0.0835   0.8150   0.0127
  -7.000  -0.3166   0.01531   0.00831  -0.0812   0.8053   0.0140
  -6.500  -0.2935   0.01422   0.00714  -0.0767   0.7883   0.0208
  -6.250  -0.2868   0.01363   0.00654  -0.0735   0.7808   0.0304
  -6.000  -0.2853   0.01306   0.00609  -0.0693   0.7724   0.0533
  -5.750  -0.2772   0.01247   0.00565  -0.0664   0.7656   0.0913
  -5.500  -0.2676   0.01185   0.00525  -0.0638   0.7585   0.1412
  -5.250  -0.2610   0.01099   0.00474  -0.0608   0.7521   0.2268
  -5.000  -0.2593   0.00969   0.00404  -0.0572   0.7461   0.3718
  -4.750  -0.2567   0.00835   0.00363  -0.0535   0.7400   0.5840
  -4.500  -0.2301   0.00857   0.00384  -0.0531   0.7349   0.6326
  -4.250  -0.2022   0.00888   0.00409  -0.0529   0.7298   0.6515
  -4.000  -0.1747   0.00912   0.00424  -0.0528   0.7244   0.6632
  -3.750  -0.1459   0.00941   0.00448  -0.0528   0.7197   0.6708
  -3.500  -0.1177   0.00964   0.00461  -0.0528   0.7153   0.6786
  -3.250  -0.0888   0.01007   0.00507  -0.0526   0.7106   0.6861
  -3.000  -0.0607   0.01047   0.00543  -0.0523   0.7060   0.6951
  -2.750  -0.0306   0.01122   0.00619  -0.0519   0.7019   0.7034
  -2.500  -0.0033   0.01138   0.00628  -0.0519   0.6975   0.7096
  -2.250   0.0245   0.01135   0.00622  -0.0520   0.6932   0.7110
  -2.000   0.0525   0.01132   0.00613  -0.0522   0.6893   0.7123
  -1.750   0.0811   0.01132   0.00605  -0.0526   0.6855   0.7135
  -1.500   0.1088   0.01128   0.00598  -0.0528   0.6815   0.7149
  -1.250   0.1365   0.01122   0.00588  -0.0530   0.6775   0.7161
  -1.000   0.1646   0.01117   0.00579  -0.0534   0.6738   0.7176
  -0.750   0.1931   0.01114   0.00568  -0.0538   0.6703   0.7190
  -0.500   0.2212   0.01108   0.00558  -0.0542   0.6667   0.7203
  -0.250   0.2490   0.01101   0.00549  -0.0546   0.6629   0.7218
   0.000   0.2772   0.01096   0.00539  -0.0550   0.6592   0.7233
   0.250   0.3058   0.01093   0.00529  -0.0556   0.6558   0.7244
   0.500   0.3346   0.01090   0.00520  -0.0561   0.6525   0.7253
   0.750   0.3617   0.01081   0.00514  -0.0562   0.6489   0.7262
   1.000   0.3894   0.01077   0.00511  -0.0564   0.6450   0.7271
   1.250   0.4174   0.01076   0.00509  -0.0567   0.6413   0.7282
   1.500   0.4463   0.01080   0.00508  -0.0572   0.6375   0.7292
   1.750   0.4732   0.01077   0.00508  -0.0573   0.6332   0.7301
   2.000   0.5006   0.01074   0.00506  -0.0574   0.6288   0.7311
   2.250   0.5286   0.01074   0.00504  -0.0577   0.6248   0.7322
   2.500   0.5574   0.01079   0.00506  -0.0582   0.6209   0.7332
   2.750   0.5840   0.01075   0.00507  -0.0583   0.6164   0.7344
   3.000   0.6113   0.01073   0.00506  -0.0584   0.6116   0.7355
   3.250   0.6394   0.01075   0.00506  -0.0588   0.6071   0.7369
   3.500   0.6666   0.01078   0.00510  -0.0589   0.6025   0.7382
   3.750   0.6934   0.01077   0.00512  -0.0590   0.5974   0.7394
   4.000   0.7209   0.01078   0.00513  -0.0592   0.5924   0.7404
   4.250   0.7478   0.01078   0.00514  -0.0593   0.5872   0.7414
   4.500   0.7733   0.01074   0.00516  -0.0591   0.5811   0.7424
   4.750   0.8000   0.01076   0.00518  -0.0591   0.5753   0.7434
   5.000   0.8253   0.01076   0.00526  -0.0589   0.5690   0.7445
   5.250   0.8507   0.01077   0.00531  -0.0586   0.5622   0.7455
   5.500   0.8760   0.01081   0.00538  -0.0583   0.5552   0.7467
   5.750   0.9005   0.01082   0.00545  -0.0579   0.5470   0.7479
   6.000   0.9247   0.01087   0.00553  -0.0574   0.5383   0.7494
   6.250   0.9482   0.01093   0.00561  -0.0568   0.5283   0.7509
   6.500   0.9714   0.01098   0.00571  -0.0562   0.5170   0.7525
   6.750   0.9937   0.01106   0.00582  -0.0554   0.5045   0.7539
   7.000   1.0145   0.01117   0.00593  -0.0543   0.4886   0.7552
   7.250   1.0333   0.01135   0.00608  -0.0528   0.4694   0.7564
   7.500   1.0487   0.01155   0.00624  -0.0507   0.4455   0.7578
   7.750   1.0582   0.01188   0.00648  -0.0475   0.4170   0.7593
   8.000   1.0635   0.01230   0.00681  -0.0435   0.3878   0.7608
   8.250   1.0687   0.01287   0.00726  -0.0397   0.3583   0.7624
   8.500   1.0741   0.01352   0.00780  -0.0362   0.3295   0.7641
   8.750   1.0789   0.01423   0.00841  -0.0327   0.3019   0.7661
   9.000   1.0831   0.01500   0.00908  -0.0292   0.2760   0.7682
   9.250   1.0866   0.01586   0.00983  -0.0259   0.2507   0.7703
   9.500   1.0920   0.01672   0.01061  -0.0231   0.2287   0.7721
   9.750   1.0964   0.01763   0.01146  -0.0203   0.2080   0.7739
  10.000   1.1001   0.01865   0.01242  -0.0175   0.1883   0.7758
  10.250   1.1052   0.01968   0.01341  -0.0152   0.1701   0.7777
  10.500   1.1100   0.02080   0.01449  -0.0129   0.1531   0.7798
  10.750   1.1142   0.02203   0.01566  -0.0108   0.1363   0.7820
  11.000   1.1185   0.02332   0.01691  -0.0088   0.1212   0.7843
  11.250   1.1227   0.02469   0.01822  -0.0070   0.1067   0.7865
  11.500   1.1279   0.02605   0.01954  -0.0054   0.0944   0.7887
  11.750   1.1325   0.02744   0.02093  -0.0038   0.0828   0.7911
  12.000   1.1376   0.02888   0.02238  -0.0023   0.0729   0.7936
  12.250   1.1423   0.03040   0.02390  -0.0010   0.0642   0.7964
  12.500   1.1460   0.03206   0.02554   0.0003   0.0561   0.7993
  12.750   1.1508   0.03371   0.02720   0.0014   0.0494   0.8022
  13.000   1.1563   0.03534   0.02886   0.0023   0.0437   0.8049
  13.250   1.1591   0.03720   0.03075   0.0034   0.0388   0.8079
  13.500   1.1647   0.03891   0.03252   0.0041   0.0348   0.8111
  13.750   1.1685   0.04084   0.03449   0.0049   0.0312   0.8146
  14.000   1.1730   0.04278   0.03647   0.0054   0.0282   0.8183
  14.250   1.1762   0.04487   0.03863   0.0060   0.0255   0.8220
  14.500   1.1804   0.04691   0.04076   0.0064   0.0232   0.8262
  14.750   1.1816   0.04932   0.04323   0.0068   0.0212   0.8309
  15.000   1.1864   0.05146   0.04547   0.0069   0.0194   0.8360
  15.250   1.1847   0.05426   0.04834   0.0071   0.0176   0.8416
  15.500   1.1912   0.05629   0.05049   0.0071   0.0160   0.8490
  15.750   1.1901   0.05917   0.05346   0.0071   0.0145   0.8575
  16.000   1.1907   0.06188   0.05631   0.0071   0.0134   0.8690
  16.250   1.1898   0.06459   0.05921   0.0073   0.0125   0.8894
  16.500   1.1953   0.06800   0.06283   0.0051   0.0117   0.9444
  16.750   1.1903   0.07167   0.06659   0.0044   0.0106   1.0000
  17.000   1.1905   0.07502   0.07004   0.0034   0.0098   1.0000
  17.250   1.1891   0.07863   0.07371   0.0023   0.0092   1.0000
  17.500   1.1793   0.08351   0.07867   0.0008   0.0086   1.0000
  17.750   1.1803   0.08696   0.08223  -0.0004   0.0082   1.0000
  18.000   1.1759   0.09125   0.08663  -0.0020   0.0078   1.0000
  18.250   1.1721   0.09556   0.09103  -0.0037   0.0075   1.0000
  18.500   1.1672   0.10011   0.09567  -0.0056   0.0070   1.0000
  18.750   1.1593   0.10523   0.10087  -0.0078   0.0067   1.0000
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