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EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 546 AIRFOIL (e546-il)
Reynolds number: 500,000
Max Cl/Cd: 87.37 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e546-il-500000.txt
Download as CSV file: xf-e546-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 546 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.3109   0.13717   0.13492  -0.0380   1.0000   0.0165
 -14.250  -0.3234   0.13114   0.12891  -0.0411   1.0000   0.0177
 -14.000  -0.4388   0.13795   0.13552  -0.0334   1.0000   0.0151
 -13.750  -0.4355   0.13450   0.13208  -0.0345   1.0000   0.0154
 -13.500  -0.4336   0.13066   0.12826  -0.0358   1.0000   0.0162
 -13.250  -0.4339   0.12605   0.12366  -0.0376   1.0000   0.0161
  -9.250  -0.6866   0.03020   0.02530  -0.0513   0.9736   0.0108
  -9.000  -0.6637   0.02704   0.02177  -0.0516   0.9660   0.0104
  -8.750  -0.6347   0.02482   0.01928  -0.0527   0.9598   0.0105
  -8.500  -0.6012   0.02284   0.01706  -0.0542   0.9546   0.0105
  -8.250  -0.5644   0.02136   0.01541  -0.0564   0.9488   0.0108
  -8.000  -0.5210   0.01986   0.01375  -0.0596   0.9454   0.0111
  -7.750  -0.4778   0.01853   0.01233  -0.0629   0.9400   0.0111
  -7.500  -0.4353   0.01738   0.01108  -0.0663   0.9312   0.0114
  -7.250  -0.3966   0.01634   0.00996  -0.0694   0.9178   0.0117
  -7.000  -0.3713   0.01524   0.00879  -0.0702   0.8985   0.0124
  -6.750  -0.3526   0.01463   0.00807  -0.0692   0.8797   0.0133
  -6.500  -0.3398   0.01417   0.00749  -0.0669   0.8626   0.0139
  -6.250  -0.3298   0.01366   0.00689  -0.0640   0.8470   0.0158
  -6.000  -0.3149   0.01325   0.00640  -0.0619   0.8335   0.0183
  -5.750  -0.3010   0.01273   0.00586  -0.0596   0.8212   0.0253
  -5.500  -0.2890   0.01208   0.00533  -0.0572   0.8098   0.0522
  -5.250  -0.2754   0.01148   0.00491  -0.0551   0.7989   0.0992
  -5.000  -0.2615   0.01082   0.00451  -0.0531   0.7882   0.1631
  -4.750  -0.2521   0.00979   0.00396  -0.0507   0.7785   0.2851
  -4.500  -0.2510   0.00798   0.00315  -0.0471   0.7685   0.5210
  -4.250  -0.2286   0.00797   0.00341  -0.0460   0.7598   0.6312
  -4.000  -0.2013   0.00821   0.00358  -0.0456   0.7511   0.6515
  -3.750  -0.1739   0.00846   0.00375  -0.0453   0.7426   0.6653
  -3.500  -0.1463   0.00874   0.00391  -0.0451   0.7346   0.6765
  -3.250  -0.1184   0.00894   0.00410  -0.0449   0.7264   0.6828
  -3.000  -0.0908   0.00923   0.00428  -0.0446   0.7184   0.6915
  -2.750  -0.0631   0.00964   0.00472  -0.0440   0.7103   0.7001
  -2.500  -0.0357   0.01009   0.00511  -0.0435   0.7027   0.7107
  -2.250  -0.0081   0.01042   0.00545  -0.0430   0.6951   0.7156
  -2.000   0.0194   0.01045   0.00540  -0.0430   0.6873   0.7180
  -1.750   0.0471   0.01042   0.00529  -0.0431   0.6800   0.7199
  -1.500   0.0747   0.01036   0.00515  -0.0433   0.6725   0.7217
  -1.250   0.1026   0.01032   0.00500  -0.0436   0.6657   0.7234
  -1.000   0.1304   0.01026   0.00487  -0.0439   0.6581   0.7249
  -0.750   0.1582   0.01022   0.00472  -0.0441   0.6515   0.7260
  -0.500   0.1857   0.01012   0.00462  -0.0442   0.6443   0.7271
  -0.250   0.2133   0.01010   0.00454  -0.0444   0.6378   0.7281
   0.000   0.2410   0.01007   0.00448  -0.0445   0.6309   0.7291
   0.250   0.2687   0.01006   0.00443  -0.0447   0.6243   0.7300
   0.500   0.2965   0.01007   0.00438  -0.0449   0.6182   0.7310
   0.750   0.3242   0.01005   0.00435  -0.0451   0.6114   0.7322
   1.000   0.3520   0.01008   0.00433  -0.0453   0.6054   0.7335
   1.250   0.3798   0.01007   0.00432  -0.0455   0.5991   0.7348
   1.500   0.4075   0.01007   0.00429  -0.0457   0.5928   0.7359
   1.750   0.4354   0.01011   0.00427  -0.0459   0.5870   0.7371
   2.000   0.4631   0.01010   0.00426  -0.0462   0.5806   0.7382
   2.250   0.4908   0.01013   0.00425  -0.0464   0.5745   0.7394
   2.500   0.5186   0.01016   0.00427  -0.0466   0.5683   0.7404
   2.750   0.5461   0.01019   0.00428  -0.0468   0.5615   0.7416
   3.000   0.5732   0.01021   0.00428  -0.0469   0.5551   0.7428
   3.250   0.6001   0.01019   0.00431  -0.0469   0.5482   0.7439
   3.500   0.6271   0.01025   0.00434  -0.0470   0.5420   0.7449
   3.750   0.6541   0.01028   0.00442  -0.0470   0.5354   0.7459
   4.000   0.6808   0.01033   0.00447  -0.0470   0.5285   0.7470
   4.250   0.7076   0.01040   0.00455  -0.0470   0.5219   0.7482
   4.500   0.7341   0.01044   0.00462  -0.0470   0.5143   0.7494
   4.750   0.7604   0.01053   0.00470  -0.0469   0.5072   0.7507
   5.000   0.7867   0.01057   0.00479  -0.0468   0.4991   0.7520
   5.250   0.8127   0.01068   0.00489  -0.0467   0.4918   0.7535
   5.500   0.8389   0.01073   0.00499  -0.0466   0.4834   0.7551
   5.750   0.8644   0.01085   0.00510  -0.0464   0.4751   0.7565
   6.000   0.8899   0.01093   0.00522  -0.0462   0.4655   0.7578
   6.250   0.9146   0.01099   0.00532  -0.0459   0.4556   0.7591
   6.500   0.9383   0.01111   0.00545  -0.0453   0.4449   0.7605
   6.750   0.9620   0.01122   0.00561  -0.0447   0.4323   0.7618
   7.000   0.9853   0.01136   0.00578  -0.0441   0.4187   0.7633
   7.250   1.0076   0.01154   0.00597  -0.0433   0.4033   0.7649
   7.500   1.0283   0.01177   0.00619  -0.0423   0.3850   0.7666
   7.750   1.0481   0.01205   0.00643  -0.0411   0.3629   0.7684
   8.000   1.0646   0.01244   0.00674  -0.0393   0.3356   0.7702
   8.250   1.0783   0.01295   0.00712  -0.0372   0.3034   0.7722
   8.500   1.0878   0.01352   0.00754  -0.0343   0.2717   0.7742
   8.750   1.0957   0.01408   0.00801  -0.0310   0.2448   0.7763
   9.000   1.1050   0.01469   0.00855  -0.0282   0.2203   0.7784
   9.250   1.1134   0.01538   0.00915  -0.0253   0.1970   0.7806
   9.500   1.1212   0.01611   0.00981  -0.0225   0.1750   0.7830
   9.750   1.1288   0.01687   0.01051  -0.0198   0.1560   0.7856
  10.000   1.1363   0.01768   0.01126  -0.0172   0.1381   0.7881
  10.250   1.1429   0.01854   0.01207  -0.0147   0.1221   0.7906
  10.500   1.1483   0.01947   0.01299  -0.0121   0.1073   0.7933
  10.750   1.1534   0.02050   0.01400  -0.0097   0.0940   0.7961
  11.000   1.1577   0.02165   0.01513  -0.0074   0.0814   0.7993
  11.250   1.1621   0.02288   0.01634  -0.0053   0.0706   0.8027
  11.500   1.1661   0.02421   0.01766  -0.0034   0.0610   0.8062
  11.750   1.1694   0.02560   0.01907  -0.0015   0.0528   0.8099
  12.000   1.1725   0.02711   0.02060   0.0001   0.0459   0.8140
  12.250   1.1744   0.02882   0.02230   0.0017   0.0403   0.8183
  12.500   1.1793   0.03036   0.02389   0.0028   0.0351   0.8226
  12.750   1.1827   0.03204   0.02565   0.0040   0.0314   0.8273
  13.000   1.1850   0.03390   0.02757   0.0051   0.0285   0.8329
  13.250   1.1899   0.03561   0.02935   0.0058   0.0253   0.8387
  13.500   1.1902   0.03773   0.03152   0.0067   0.0229   0.8456
  13.750   1.1959   0.03946   0.03336   0.0073   0.0206   0.8539
  14.000   1.1956   0.04173   0.03572   0.0080   0.0188   0.8649
  14.250   1.1994   0.04363   0.03779   0.0086   0.0172   0.8810
  14.500   1.2000   0.04596   0.04031   0.0089   0.0158   0.9233
  14.750   1.2064   0.04863   0.04312   0.0075   0.0143   1.0000
  15.000   1.2076   0.05138   0.04591   0.0071   0.0127   1.0000
  15.250   1.2078   0.05429   0.04890   0.0067   0.0116   1.0000
  15.500   1.2066   0.05743   0.05209   0.0062   0.0100   1.0000
  15.750   1.2057   0.06064   0.05538   0.0056   0.0092   1.0000
  16.000   1.2039   0.06404   0.05887   0.0048   0.0082   1.0000
  16.250   1.1995   0.06785   0.06274   0.0038   0.0076   1.0000
  16.500   1.1979   0.07141   0.06641   0.0028   0.0066   1.0000
  16.750   1.1936   0.07544   0.07054   0.0016   0.0064   1.0000
  17.000   1.1896   0.07949   0.07468   0.0002   0.0061   1.0000
  17.250   1.1792   0.08462   0.07991  -0.0017   0.0056   1.0000
  17.500   1.1736   0.08917   0.08458  -0.0034   0.0054   1.0000
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