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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 100,000
Max Cl/Cd: 29.91 at α=13.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e584-il-100000.txt
Download as CSV file: xf-e584-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1889   0.12690   0.12245  -0.0747   0.9688   0.0803
 -11.250  -0.1893   0.12326   0.11883  -0.0824   0.9610   0.0836
 -11.000  -0.1847   0.11807   0.11367  -0.0891   0.9560   0.0851
 -10.750  -0.1509   0.11353   0.10908  -0.0884   0.9508   0.0879
 -10.500  -0.1316   0.10942   0.10494  -0.0925   0.9467   0.0919
 -10.250  -0.1333   0.10524   0.10078  -0.1013   0.9413   0.0968
 -10.000  -0.1272   0.10001   0.09557  -0.1059   0.9352   0.0990
  -9.750  -0.0942   0.09619   0.09170  -0.1065   0.9324   0.1028
  -9.500  -0.0801   0.09181   0.08729  -0.1124   0.9290   0.1088
  -9.250  -0.1219   0.08717   0.08267  -0.1254   0.9159   0.1120
  -9.000  -0.0661   0.08337   0.07885  -0.1202   0.9159   0.1168
  -8.750  -0.0552   0.07959   0.07504  -0.1243   0.9107   0.1231
  -8.500  -0.1040   0.07610   0.07150  -0.1308   0.8977   0.1268
  -8.250  -0.1470   0.07611   0.07142  -0.1268   0.8857   0.1273
  -8.000  -0.0775   0.06986   0.06531  -0.1295   0.8870   0.1344
  -7.750  -0.0972   0.06768   0.06304  -0.1291   0.8804   0.1402
  -7.500  -0.1422   0.06834   0.06362  -0.1229   0.8690   0.1422
  -5.750  -0.2151   0.05031   0.04380  -0.0959   0.8292   0.0744
  -5.250  -0.2632   0.04975   0.04292  -0.0800   0.8156   0.0640
  -5.000  -0.2370   0.04655   0.03925  -0.0798   0.8133   0.0587
  -4.750  -0.2313   0.04519   0.03756  -0.0766   0.8093   0.0580
  -4.500  -0.2481   0.04545   0.03769  -0.0703   0.8037   0.0578
  -4.250  -0.2308   0.04371   0.03555  -0.0686   0.8003   0.0568
  -4.000  -0.1996   0.04145   0.03273  -0.0684   0.7976   0.0552
  -3.750  -0.1593   0.03948   0.03040  -0.0697   0.7955   0.0557
  -3.500  -0.1618   0.03977   0.03060  -0.0655   0.7912   0.0566
  -3.250  -0.1571   0.03976   0.03050  -0.0623   0.7866   0.0578
  -3.000  -0.1334   0.03907   0.02963  -0.0614   0.7830   0.0629
  -2.750  -0.1007   0.03828   0.02881  -0.0620   0.7802   0.0725
  -2.500  -0.0645   0.03695   0.02774  -0.0630   0.7781   0.0929
  -2.250  -0.0826   0.03809   0.02883  -0.0570   0.7721   0.0969
  -2.000   0.4669   0.03089   0.02367  -0.1332   0.7881   1.0000
  -1.750   0.4658   0.03177   0.02448  -0.1295   0.7825   1.0000
  -1.500   0.4917   0.03168   0.02424  -0.1297   0.7795   1.0000
  -1.250   0.4161   0.03518   0.02790  -0.1145   0.7681   1.0000
  -1.000   0.4368   0.03538   0.02797  -0.1140   0.7645   1.0000
  -0.750   0.3621   0.03836   0.03107  -0.0989   0.7540   1.0000
  -0.500   0.3632   0.03915   0.03179  -0.0954   0.7489   1.0000
  -0.250   0.4005   0.03895   0.03143  -0.0972   0.7461   1.0000
   0.000   0.4386   0.03882   0.03115  -0.0991   0.7435   1.0000
   0.250   0.3541   0.04200   0.03446  -0.0835   0.7317   1.0000
   0.500   0.3941   0.04180   0.03412  -0.0854   0.7290   1.0000
   0.750   0.3414   0.04412   0.03649  -0.0748   0.7194   1.0000
   1.000   0.3621   0.04444   0.03672  -0.0741   0.7150   1.0000
   1.250   0.4064   0.04419   0.03634  -0.0764   0.7123   1.0000
   1.500   0.3526   0.04650   0.03870  -0.0661   0.7023   1.0000
   1.750   0.3837   0.04658   0.03868  -0.0665   0.6985   1.0000
   2.000   0.3621   0.04806   0.04016  -0.0605   0.6904   1.0000
   2.250   0.3767   0.04856   0.04060  -0.0590   0.6852   1.0000
   2.500   0.4199   0.04836   0.04030  -0.0608   0.6822   1.0000
   2.750   0.3809   0.05024   0.04221  -0.0528   0.6720   1.0000
   3.000   0.4183   0.05016   0.04205  -0.0538   0.6683   1.0000
   3.250   0.3898   0.05180   0.04371  -0.0473   0.6587   1.0000
   3.500   0.4225   0.05179   0.04363  -0.0476   0.6544   1.0000
   3.750   0.4012   0.05325   0.04510  -0.0421   0.6451   1.0000
   4.000   0.4301   0.05330   0.04510  -0.0419   0.6404   1.0000
   4.250   0.4141   0.05457   0.04637  -0.0370   0.6309   1.0000
   4.500   0.4402   0.05468   0.04644  -0.0365   0.6262   1.0000
   4.750   0.4272   0.05588   0.04764  -0.0321   0.6168   1.0000
   5.000   0.4555   0.05587   0.04759  -0.0317   0.6120   1.0000
   5.250   0.4451   0.05717   0.04889  -0.0280   0.6023   1.0000
   5.500   0.4764   0.05715   0.04886  -0.0282   0.5978   1.0000
   5.750   0.4720   0.05861   0.05033  -0.0257   0.5879   1.0000
   6.000   0.5066   0.05851   0.05022  -0.0262   0.5834   1.0000
   6.250   0.5055   0.06010   0.05183  -0.0244   0.5731   1.0000
   6.500   0.5400   0.06004   0.05177  -0.0250   0.5688   1.0000
   6.750   0.5408   0.06177   0.05353  -0.0237   0.5584   1.0000
   7.000   0.5760   0.06160   0.05338  -0.0243   0.5538   1.0000
   7.250   0.6217   0.06082   0.05261  -0.0255   0.5514   1.0000
   7.500   0.6119   0.06327   0.05511  -0.0238   0.5385   1.0000
   7.750   0.6563   0.06241   0.05430  -0.0248   0.5360   1.0000
   8.000   0.6486   0.06494   0.05687  -0.0234   0.5230   1.0000
   8.250   0.6930   0.06388   0.05586  -0.0243   0.5205   1.0000
   8.500   0.6873   0.06644   0.05847  -0.0231   0.5076   1.0000
   8.750   0.7315   0.06521   0.05732  -0.0239   0.5051   1.0000
   9.000   0.7267   0.06784   0.06000  -0.0229   0.4922   1.0000
   9.250   0.7356   0.06950   0.06172  -0.0225   0.4824   1.0000
   9.500   0.7667   0.06912   0.06143  -0.0227   0.4767   1.0000
   9.750   0.8118   0.06740   0.05980  -0.0231   0.4743   1.0000
  10.000   0.8072   0.07026   0.06272  -0.0224   0.4611   1.0000
  10.250   0.8313   0.07039   0.06295  -0.0222   0.4543   1.0000
  10.500   0.8483   0.07116   0.06381  -0.0220   0.4455   1.0000
  10.750   0.8675   0.07172   0.06446  -0.0217   0.4375   1.0000
  11.000   0.9432   0.06596   0.05888  -0.0222   0.4413   1.0000
  11.500   0.9812   0.06638   0.05952  -0.0212   0.4245   1.0000
  11.750   1.0457   0.06100   0.05432  -0.0212   0.4250   1.0000
  12.000   1.1201   0.05479   0.04832  -0.0217   0.4249   1.0000
  12.250   1.0469   0.06548   0.05898  -0.0196   0.3995   1.0000
  12.500   1.1336   0.05738   0.05111  -0.0198   0.4003   1.0000
  12.750   1.2775   0.04479   0.03873  -0.0228   0.3973   1.0000
  13.000   1.3005   0.04447   0.03847  -0.0222   0.3825   1.0000
  13.250   1.3223   0.04429   0.03830  -0.0215   0.3666   1.0000
  13.500   1.3373   0.04471   0.03873  -0.0206   0.3502   1.0000
  13.750   1.3476   0.04556   0.03957  -0.0195   0.3335   1.0000
  14.000   1.3549   0.04673   0.04071  -0.0183   0.3168   1.0000
  14.250   1.3616   0.04800   0.04193  -0.0172   0.2999   1.0000
  14.500   1.3600   0.05006   0.04397  -0.0159   0.2839   1.0000
  14.750   1.3574   0.05232   0.04621  -0.0148   0.2681   1.0000
  15.000   1.3545   0.05469   0.04857  -0.0138   0.2526   1.0000
  15.250   1.3509   0.05724   0.05110  -0.0129   0.2374   1.0000
  15.500   1.3469   0.05991   0.05374  -0.0121   0.2224   1.0000
  15.750   1.3404   0.06297   0.05683  -0.0115   0.2084   1.0000
  16.000   1.3322   0.06635   0.06025  -0.0111   0.1950   1.0000
  16.250   1.3256   0.06970   0.06362  -0.0108   0.1818   1.0000
  16.500   1.3193   0.07313   0.06707  -0.0107   0.1690   1.0000
  16.750   1.3137   0.07657   0.07051  -0.0108   0.1566   1.0000
  17.000   1.3094   0.07994   0.07385  -0.0109   0.1450   1.0000
  17.250   1.3066   0.08317   0.07701  -0.0111   0.1336   1.0000
  17.500   1.3055   0.08622   0.07996  -0.0113   0.1222   1.0000
  17.750   1.2942   0.09095   0.08491  -0.0122   0.1138   1.0000
  18.000   1.2912   0.09449   0.08846  -0.0128   0.1048   1.0000
  18.250   1.2923   0.09740   0.09126  -0.0132   0.0956   1.0000
  18.500   1.2845   0.10187   0.09591  -0.0144   0.0890   1.0000
  18.750   1.2838   0.10521   0.09927  -0.0151   0.0820   1.0000
  19.000   1.2856   0.10817   0.10216  -0.0159   0.0752   1.0000
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