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

EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 479 AIRFOIL (e479-il)
Reynolds number: 100,000
Max Cl/Cd: 33.08 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e479-il-100000.txt
Download as CSV file: xf-e479-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 479 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.0729   0.06284   0.05659  -0.0362   1.0000   0.1489
 -14.000  -1.1318   0.05491   0.04836  -0.0386   1.0000   0.1491
 -13.750  -1.1736   0.05007   0.04319  -0.0379   1.0000   0.1501
 -13.500  -1.1189   0.05145   0.04490  -0.0375   1.0000   0.1578
 -13.250  -1.1435   0.04796   0.04120  -0.0363   1.0000   0.1606
 -13.000  -1.1713   0.04494   0.03791  -0.0334   1.0000   0.1630
 -12.750  -1.1899   0.04263   0.03535  -0.0296   1.0000   0.1660
 -12.500  -1.1522   0.04263   0.03562  -0.0302   1.0000   0.1731
 -12.250  -1.1645   0.04064   0.03337  -0.0268   1.0000   0.1775
 -12.000  -1.1539   0.03923   0.03193  -0.0253   1.0000   0.1829
 -11.750  -1.1368   0.03858   0.03132  -0.0241   1.0000   0.1892
 -11.500  -1.1453   0.03665   0.02897  -0.0207   1.0000   0.1946
 -11.250  -1.1131   0.03635   0.02896  -0.0209   1.0000   0.2014
 -11.000  -1.1089   0.03501   0.02738  -0.0185   1.0000   0.2081
 -10.750  -1.0870   0.03429   0.02676  -0.0177   1.0000   0.2147
 -10.500  -1.0735   0.03345   0.02581  -0.0160   1.0000   0.2220
 -10.250  -1.0566   0.03256   0.02488  -0.0147   1.0000   0.2291
 -10.000  -1.0378   0.03201   0.02431  -0.0135   1.0000   0.2367
  -9.750  -1.0222   0.03108   0.02329  -0.0120   1.0000   0.2442
  -9.500  -1.0010   0.03069   0.02293  -0.0109   1.0000   0.2520
  -9.250  -0.9852   0.02978   0.02190  -0.0093   1.0000   0.2598
  -9.000  -0.9629   0.02946   0.02164  -0.0083   1.0000   0.2678
  -8.750  -0.9463   0.02863   0.02071  -0.0068   1.0000   0.2759
  -8.500  -0.9240   0.02831   0.02043  -0.0057   1.0000   0.2839
  -8.250  -0.9067   0.02756   0.01959  -0.0042   1.0000   0.2923
  -8.000  -0.8847   0.02724   0.01932  -0.0031   1.0000   0.3004
  -7.750  -0.8671   0.02653   0.01853  -0.0016   1.0000   0.3088
  -7.500  -0.8454   0.02622   0.01827  -0.0004   1.0000   0.3170
  -7.250  -0.8279   0.02555   0.01753   0.0012   1.0000   0.3255
  -7.000  -0.8066   0.02524   0.01728   0.0024   1.0000   0.3336
  -6.750  -0.7894   0.02463   0.01659   0.0041   1.0000   0.3422
  -6.500  -0.7690   0.02433   0.01637   0.0054   1.0000   0.3502
  -6.250  -0.7535   0.02374   0.01571   0.0072   1.0000   0.3588
  -6.000  -0.7350   0.02350   0.01557   0.0088   1.0000   0.3664
  -5.750  -0.7235   0.02297   0.01493   0.0111   1.0000   0.3750
  -5.500  -0.7087   0.02279   0.01489   0.0131   1.0000   0.3817
  -5.250  -0.7023   0.02241   0.01433   0.0157   1.0000   0.3905
  -5.000  -0.6797   0.02232   0.01444   0.0159   0.9971   0.3975
  -4.750  -0.6229   0.02205   0.01411   0.0099   0.9818   0.4107
  -4.500  -0.5679   0.02179   0.01381   0.0044   0.9663   0.4237
  -4.250  -0.5131   0.02151   0.01365  -0.0005   0.9509   0.4345
  -4.000  -0.4601   0.02107   0.01318  -0.0051   0.9351   0.4466
  -3.750  -0.4147   0.02067   0.01270  -0.0083   0.9158   0.4591
  -3.500  -0.3711   0.02036   0.01250  -0.0105   0.8948   0.4685
  -3.250  -0.3352   0.02000   0.01203  -0.0116   0.8719   0.4795
  -3.000  -0.3030   0.01981   0.01183  -0.0115   0.8489   0.4892
  -2.750  -0.2770   0.01960   0.01155  -0.0106   0.8235   0.4987
  -2.500  -0.2512   0.01946   0.01133  -0.0096   0.8006   0.5087
  -2.250  -0.2256   0.01932   0.01113  -0.0085   0.7795   0.5180
  -2.000  -0.2020   0.01920   0.01088  -0.0074   0.7575   0.5291
  -1.750  -0.1765   0.01912   0.01083  -0.0063   0.7370   0.5381
  -1.500  -0.1521   0.01901   0.01062  -0.0053   0.7178   0.5495
  -1.250  -0.1268   0.01896   0.01056  -0.0043   0.6995   0.5600
  -1.000  -0.1015   0.01889   0.01046  -0.0034   0.6824   0.5711
  -0.750  -0.0766   0.01884   0.01031  -0.0025   0.6662   0.5840
  -0.500  -0.0508   0.01882   0.01030  -0.0016   0.6510   0.5955
  -0.250  -0.0251   0.01879   0.01023  -0.0008   0.6368   0.6080
   0.000   0.0000   0.01877   0.01022   0.0000   0.6219   0.6219
   0.250   0.0251   0.01879   0.01023   0.0008   0.6080   0.6368
   0.500   0.0508   0.01882   0.01030   0.0016   0.5955   0.6510
   0.750   0.0766   0.01884   0.01031   0.0025   0.5840   0.6662
   1.000   0.1015   0.01889   0.01045   0.0034   0.5711   0.6824
   1.250   0.1268   0.01896   0.01056   0.0043   0.5600   0.6995
   1.500   0.1521   0.01901   0.01062   0.0053   0.5495   0.7178
   1.750   0.1765   0.01912   0.01084   0.0063   0.5381   0.7370
   2.000   0.2020   0.01920   0.01088   0.0074   0.5291   0.7575
   2.250   0.2256   0.01932   0.01113   0.0085   0.5180   0.7795
   2.500   0.2512   0.01946   0.01133   0.0096   0.5087   0.8006
   2.750   0.2770   0.01960   0.01155   0.0106   0.4986   0.8235
   3.000   0.3030   0.01981   0.01183   0.0115   0.4892   0.8489
   3.250   0.3352   0.02000   0.01203   0.0116   0.4795   0.8719
   3.500   0.3711   0.02036   0.01250   0.0105   0.4685   0.8947
   3.750   0.4146   0.02067   0.01270   0.0083   0.4591   0.9158
   4.000   0.4601   0.02107   0.01318   0.0051   0.4467   0.9352
   4.250   0.5130   0.02152   0.01365   0.0005   0.4346   0.9510
   4.500   0.5679   0.02179   0.01381  -0.0044   0.4237   0.9663
   4.750   0.6230   0.02205   0.01410  -0.0099   0.4106   0.9819
   5.000   0.6798   0.02231   0.01443  -0.0159   0.3974   0.9972
   5.250   0.7021   0.02240   0.01433  -0.0157   0.3906   1.0000
   5.500   0.7086   0.02279   0.01489  -0.0131   0.3817   1.0000
   5.750   0.7233   0.02297   0.01494  -0.0111   0.3750   1.0000
   6.000   0.7349   0.02350   0.01557  -0.0088   0.3665   1.0000
   6.250   0.7534   0.02374   0.01572  -0.0072   0.3588   1.0000
   6.500   0.7689   0.02433   0.01636  -0.0054   0.3502   1.0000
   6.750   0.7893   0.02462   0.01659  -0.0040   0.3422   1.0000
   7.000   0.8066   0.02524   0.01728  -0.0024   0.3336   1.0000
   7.250   0.8278   0.02556   0.01753  -0.0012   0.3255   1.0000
   7.500   0.8454   0.02622   0.01827   0.0004   0.3170   1.0000
   7.750   0.8671   0.02654   0.01854   0.0016   0.3088   1.0000
   8.000   0.8847   0.02724   0.01931   0.0031   0.3004   1.0000
   8.250   0.9067   0.02757   0.01960   0.0042   0.2923   1.0000
   8.500   0.9240   0.02831   0.02043   0.0057   0.2839   1.0000
   8.750   0.9463   0.02863   0.02070   0.0068   0.2759   1.0000
   9.000   0.9630   0.02946   0.02163   0.0083   0.2678   1.0000
   9.250   0.9852   0.02978   0.02191   0.0093   0.2598   1.0000
   9.500   1.0011   0.03069   0.02293   0.0109   0.2520   1.0000
   9.750   1.0223   0.03108   0.02329   0.0119   0.2442   1.0000
  10.000   1.0380   0.03201   0.02431   0.0134   0.2367   1.0000
  10.250   1.0567   0.03255   0.02487   0.0147   0.2291   1.0000
  10.500   1.0738   0.03345   0.02580   0.0160   0.2221   1.0000
  10.750   1.0871   0.03430   0.02676   0.0177   0.2148   1.0000
  11.000   1.1091   0.03501   0.02738   0.0185   0.2081   1.0000
  11.250   1.1134   0.03634   0.02895   0.0209   0.2014   1.0000
  11.500   1.1455   0.03665   0.02897   0.0207   0.1946   1.0000
  11.750   1.1371   0.03858   0.03132   0.0241   0.1891   1.0000
  12.000   1.1546   0.03922   0.03191   0.0252   0.1828   1.0000
  12.250   1.1646   0.04063   0.03337   0.0268   0.1774   1.0000
  12.500   1.1528   0.04263   0.03562   0.0301   0.1731   1.0000
  12.750   1.1928   0.04259   0.03528   0.0294   0.1658   1.0000
  13.000   1.1716   0.04496   0.03793   0.0333   0.1630   1.0000
  13.250   1.1440   0.04796   0.04120   0.0363   0.1604   1.0000
  13.500   1.1201   0.05143   0.04487   0.0374   0.1577   1.0000
  13.750   1.1736   0.05010   0.04323   0.0378   0.1501   1.0000
  14.000   1.1321   0.05496   0.04841   0.0384   0.1490   1.0000
  14.250   1.0725   0.06300   0.05676   0.0359   0.1489   1.0000
<< Back to EPPLER 479 AIRFOIL (e479-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 479 AIRFOIL (e479-il)