Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 544 AIRFOIL (e544-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.07 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e544-il-1000000-n5.txt
Download as CSV file: xf-e544-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.5936   0.12789   0.12598  -0.0414   1.0000   0.0022
 -16.500  -0.6983   0.09898   0.09680  -0.0540   1.0000   0.0021
 -16.250  -0.7488   0.08314   0.08071  -0.0627   1.0000   0.0021
 -16.000  -0.7775   0.07368   0.07106  -0.0680   1.0000   0.0021
 -15.750  -0.7907   0.06790   0.06516  -0.0708   1.0000   0.0020
 -15.500  -0.8187   0.06059   0.05763  -0.0735   1.0000   0.0021
 -15.250  -0.8244   0.05696   0.05391  -0.0744   1.0000   0.0020
 -15.000  -0.8459   0.05171   0.04845  -0.0750   1.0000   0.0020
 -14.750  -0.8481   0.04904   0.04569  -0.0750   1.0000   0.0020
 -14.500  -0.8593   0.04557   0.04205  -0.0744   1.0000   0.0020
 -14.250  -0.8643   0.04296   0.03931  -0.0736   1.0000   0.0020
 -14.000  -0.8721   0.04019   0.03639  -0.0723   1.0000   0.0020
 -13.750  -0.8740   0.03810   0.03418  -0.0710   1.0000   0.0020
 -13.250  -0.8505   0.03373   0.02953  -0.0732   0.9968   0.0020
 -13.000  -0.8481   0.03172   0.02739  -0.0718   0.9862   0.0021
 -12.750  -0.8310   0.03003   0.02557  -0.0729   0.9612   0.0021
 -12.500  -0.7945   0.02787   0.02322  -0.0784   0.9488   0.0021
 -12.250  -0.7474   0.02592   0.02108  -0.0857   0.9381   0.0021
 -12.000  -0.6940   0.02415   0.01911  -0.0940   0.9231   0.0021
 -11.750  -0.6542   0.02290   0.01763  -0.0989   0.8935   0.0022
 -11.500  -0.6364   0.02221   0.01677  -0.0986   0.8667   0.0022
 -11.250  -0.6243   0.02145   0.01585  -0.0972   0.8470   0.0022
 -11.000  -0.6117   0.02075   0.01502  -0.0957   0.8311   0.0022
 -10.750  -0.5989   0.02006   0.01422  -0.0942   0.8175   0.0022
 -10.500  -0.5848   0.01945   0.01352  -0.0928   0.8053   0.0023
 -10.250  -0.5706   0.01887   0.01285  -0.0914   0.7936   0.0023
 -10.000  -0.5561   0.01830   0.01218  -0.0900   0.7832   0.0023
  -9.750  -0.5399   0.01780   0.01162  -0.0888   0.7745   0.0023
  -9.250  -0.5125   0.01656   0.01023  -0.0856   0.7577   0.0025
  -9.000  -0.4984   0.01600   0.00959  -0.0840   0.7495   0.0026
  -8.750  -0.4820   0.01555   0.00910  -0.0827   0.7420   0.0027
  -8.500  -0.4664   0.01510   0.00859  -0.0812   0.7342   0.0029
  -8.250  -0.4498   0.01469   0.00813  -0.0799   0.7275   0.0030
  -8.000  -0.4334   0.01428   0.00768  -0.0785   0.7206   0.0033
  -7.750  -0.4175   0.01388   0.00723  -0.0770   0.7147   0.0036
  -7.500  -0.4010   0.01350   0.00681  -0.0756   0.7087   0.0039
  -7.250  -0.3854   0.01313   0.00639  -0.0740   0.7027   0.0039
  -7.000  -0.3715   0.01274   0.00596  -0.0720   0.6973   0.0042
  -6.750  -0.3592   0.01240   0.00560  -0.0697   0.6913   0.0049
  -6.500  -0.3463   0.01218   0.00533  -0.0673   0.6856   0.0055
  -6.250  -0.3282   0.01194   0.00506  -0.0658   0.6806   0.0061
  -6.000  -0.3092   0.01168   0.00479  -0.0645   0.6756   0.0079
  -5.750  -0.2896   0.01145   0.00454  -0.0634   0.6709   0.0102
  -5.500  -0.2689   0.01121   0.00430  -0.0624   0.6667   0.0136
  -5.250  -0.2478   0.01096   0.00406  -0.0615   0.6621   0.0200
  -5.000  -0.2269   0.01070   0.00383  -0.0605   0.6573   0.0306
  -4.750  -0.2063   0.01042   0.00361  -0.0595   0.6528   0.0468
  -4.500  -0.1862   0.01003   0.00335  -0.0586   0.6489   0.0785
  -4.250  -0.1669   0.00957   0.00309  -0.0575   0.6449   0.1292
  -4.000  -0.1501   0.00891   0.00275  -0.0561   0.6410   0.2135
  -3.500  -0.1173   0.00712   0.00188  -0.0535   0.6336   0.4659
  -3.250  -0.0960   0.00648   0.00166  -0.0528   0.6298   0.5854
  -3.000  -0.0684   0.00646   0.00168  -0.0529   0.6259   0.6165
  -2.750  -0.0402   0.00651   0.00170  -0.0531   0.6224   0.6331
  -2.500  -0.0114   0.00658   0.00174  -0.0534   0.6194   0.6448
  -2.250   0.0173   0.00666   0.00183  -0.0537   0.6161   0.6544
  -2.000   0.0462   0.00675   0.00185  -0.0540   0.6124   0.6604
  -1.750   0.0747   0.00676   0.00182  -0.0544   0.6089   0.6616
  -1.250   0.1321   0.00676   0.00176  -0.0551   0.6029   0.6634
  -1.000   0.1610   0.00677   0.00175  -0.0555   0.5998   0.6644
  -0.750   0.1897   0.00678   0.00174  -0.0558   0.5964   0.6654
  -0.500   0.2182   0.00681   0.00173  -0.0561   0.5932   0.6663
   0.000   0.2754   0.00685   0.00173  -0.0568   0.5871   0.6679
   0.250   0.3042   0.00687   0.00174  -0.0572   0.5840   0.6688
   0.500   0.3327   0.00690   0.00175  -0.0576   0.5803   0.6697
   0.750   0.3608   0.00694   0.00176  -0.0578   0.5762   0.6705
   1.000   0.3891   0.00697   0.00178  -0.0581   0.5720   0.6714
   1.250   0.4176   0.00700   0.00180  -0.0584   0.5673   0.6725
   1.500   0.4457   0.00704   0.00182  -0.0587   0.5628   0.6735
   1.750   0.4734   0.00710   0.00186  -0.0589   0.5586   0.6744
   2.000   0.5020   0.00713   0.00189  -0.0593   0.5546   0.6751
   2.250   0.5301   0.00717   0.00192  -0.0595   0.5493   0.6758
   2.500   0.5575   0.00724   0.00197  -0.0597   0.5441   0.6765
   2.750   0.5855   0.00727   0.00201  -0.0599   0.5392   0.6773
   3.000   0.6132   0.00731   0.00206  -0.0601   0.5336   0.6783
   3.250   0.6400   0.00738   0.00212  -0.0601   0.5274   0.6792
   3.500   0.6678   0.00742   0.00219  -0.0604   0.5209   0.6801
   3.750   0.6943   0.00751   0.00226  -0.0603   0.5126   0.6810
   4.000   0.7214   0.00758   0.00234  -0.0604   0.5043   0.6819
   4.250   0.7473   0.00768   0.00243  -0.0603   0.4940   0.6829
   4.500   0.7731   0.00780   0.00253  -0.0601   0.4823   0.6839
   4.750   0.7982   0.00793   0.00264  -0.0598   0.4683   0.6851
   5.000   0.8217   0.00813   0.00278  -0.0592   0.4500   0.6862
   5.250   0.8443   0.00837   0.00294  -0.0585   0.4272   0.6873
   5.500   0.8645   0.00870   0.00316  -0.0573   0.3992   0.6883
   5.750   0.8830   0.00908   0.00342  -0.0559   0.3685   0.6893
   6.000   0.9014   0.00946   0.00368  -0.0544   0.3418   0.6902
   6.250   0.9195   0.00984   0.00396  -0.0529   0.3159   0.6911
   6.500   0.9364   0.01022   0.00424  -0.0511   0.2919   0.6920
   6.750   0.9504   0.01060   0.00452  -0.0488   0.2681   0.6928
   7.000   0.9641   0.01095   0.00481  -0.0464   0.2484   0.6941
   7.250   0.9765   0.01138   0.00516  -0.0439   0.2255   0.6953
   7.500   0.9880   0.01188   0.00557  -0.0413   0.2040   0.6965
   7.750   1.0009   0.01233   0.00596  -0.0389   0.1854   0.6977
   8.000   1.0117   0.01287   0.00642  -0.0363   0.1654   0.6990
   8.250   1.0228   0.01340   0.00690  -0.0338   0.1488   0.7005
   8.500   1.0330   0.01399   0.00742  -0.0313   0.1328   0.7019
   8.750   1.0441   0.01457   0.00796  -0.0290   0.1196   0.7033
   9.000   1.0551   0.01518   0.00853  -0.0269   0.1073   0.7046
   9.250   1.0665   0.01580   0.00913  -0.0248   0.0971   0.7058
   9.500   1.0767   0.01651   0.00981  -0.0227   0.0868   0.7070
   9.750   1.0866   0.01727   0.01054  -0.0207   0.0773   0.7080
  10.000   1.0951   0.01814   0.01137  -0.0186   0.0672   0.7092
  10.250   1.1048   0.01897   0.01220  -0.0168   0.0591   0.7107
  10.500   1.1143   0.01987   0.01309  -0.0150   0.0514   0.7121
  10.750   1.1240   0.02079   0.01402  -0.0134   0.0456   0.7136
  11.000   1.1322   0.02184   0.01506  -0.0117   0.0391   0.7151
  11.250   1.1415   0.02286   0.01608  -0.0102   0.0340   0.7166
  11.500   1.1509   0.02391   0.01715  -0.0088   0.0298   0.7182
  11.750   1.1596   0.02505   0.01829  -0.0075   0.0262   0.7197
  12.000   1.1671   0.02629   0.01954  -0.0061   0.0219   0.7213
  12.250   1.1767   0.02744   0.02071  -0.0050   0.0192   0.7230
  12.500   1.1852   0.02870   0.02199  -0.0039   0.0169   0.7244
  12.750   1.1921   0.03008   0.02339  -0.0027   0.0140   0.7262
  13.000   1.2020   0.03130   0.02466  -0.0019   0.0129   0.7280
  13.250   1.2083   0.03281   0.02620  -0.0009   0.0103   0.7298
  13.500   1.2174   0.03417   0.02761  -0.0001   0.0096   0.7317
  13.750   1.2251   0.03566   0.02914   0.0006   0.0083   0.7336
  14.000   1.2334   0.03715   0.03068   0.0013   0.0076   0.7355
  14.250   1.2392   0.03889   0.03246   0.0019   0.0061   0.7374
  14.500   1.2470   0.04050   0.03412   0.0024   0.0056   0.7392
  15.000   1.2602   0.04405   0.03779   0.0033   0.0046   0.7431
  15.250   1.2669   0.04588   0.03969   0.0036   0.0041   0.7454
  15.500   1.2724   0.04788   0.04175   0.0038   0.0038   0.7477
  15.750   1.2769   0.05001   0.04395   0.0040   0.0034   0.7501
  16.000   1.2826   0.05207   0.04608   0.0041   0.0031   0.7526
  16.250   1.2870   0.05432   0.04840   0.0040   0.0028   0.7551
  16.750   1.2948   0.05909   0.05333   0.0038   0.0025   0.7607
  17.000   1.2966   0.06177   0.05609   0.0035   0.0022   0.7640
  17.250   1.3003   0.06430   0.05871   0.0031   0.0021   0.7673
  17.500   1.3022   0.06714   0.06164   0.0026   0.0019   0.7705
  18.000   1.3051   0.07305   0.06774   0.0013   0.0018   0.7773
  18.250   1.3054   0.07626   0.07105   0.0004   0.0017   0.7812
  18.500   1.3035   0.07984   0.07473  -0.0006   0.0015   0.7850
  19.000   1.2995   0.08729   0.08238  -0.0031   0.0014   0.7934
  19.250   1.2967   0.09123   0.08643  -0.0046   0.0013   0.7983
<< Back to EPPLER 544 AIRFOIL (e544-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 544 AIRFOIL (e544-il)