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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 500,000
Max Cl/Cd: 69.49 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e472-il-500000.txt
Download as CSV file: xf-e472-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 472 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.2089   0.08619   0.08243  -0.0227   1.0000   0.0395
 -17.500  -1.2392   0.07839   0.07452  -0.0268   1.0000   0.0399
 -17.250  -1.2722   0.07024   0.06624  -0.0311   1.0000   0.0402
 -17.000  -1.3058   0.06194   0.05780  -0.0356   1.0000   0.0404
 -16.750  -1.3374   0.05376   0.04945  -0.0404   1.0000   0.0404
 -16.500  -1.3589   0.04693   0.04244  -0.0446   1.0000   0.0410
 -16.250  -1.3714   0.04172   0.03706  -0.0478   1.0000   0.0420
 -16.000  -1.3812   0.03745   0.03263  -0.0500   1.0000   0.0430
 -15.750  -1.3938   0.03365   0.02873  -0.0509   1.0000   0.0443
 -15.500  -1.3988   0.03117   0.02618  -0.0504   1.0000   0.0456
 -15.250  -1.3989   0.02941   0.02432  -0.0491   1.0000   0.0472
 -15.000  -1.3934   0.02820   0.02300  -0.0475   1.0000   0.0489
 -14.750  -1.3931   0.02682   0.02154  -0.0451   1.0000   0.0507
 -14.500  -1.3908   0.02569   0.02037  -0.0424   1.0000   0.0527
 -14.250  -1.3838   0.02488   0.01949  -0.0398   1.0000   0.0547
 -14.000  -1.3738   0.02427   0.01878  -0.0373   1.0000   0.0567
 -13.750  -1.3704   0.02344   0.01790  -0.0338   1.0000   0.0586
 -13.500  -1.3623   0.02267   0.01712  -0.0310   1.0000   0.0608
 -13.250  -1.3484   0.02209   0.01649  -0.0289   1.0000   0.0631
 -13.000  -1.3321   0.02162   0.01591  -0.0271   1.0000   0.0652
 -12.750  -1.3196   0.02089   0.01514  -0.0248   1.0000   0.0677
 -12.500  -1.3048   0.02029   0.01454  -0.0228   1.0000   0.0702
 -12.250  -1.2868   0.01986   0.01405  -0.0211   1.0000   0.0728
 -12.000  -1.2674   0.01950   0.01359  -0.0197   1.0000   0.0750
 -11.750  -1.2524   0.01882   0.01289  -0.0176   1.0000   0.0778
 -11.500  -1.2343   0.01835   0.01242  -0.0159   1.0000   0.0806
 -11.250  -1.2142   0.01801   0.01203  -0.0145   1.0000   0.0835
 -11.000  -1.1929   0.01773   0.01164  -0.0132   1.0000   0.0857
 -10.750  -1.1760   0.01711   0.01105  -0.0114   1.0000   0.0892
 -10.500  -1.1554   0.01678   0.01071  -0.0100   1.0000   0.0924
 -10.250  -1.1334   0.01655   0.01042  -0.0088   1.0000   0.0956
 -10.000  -1.1128   0.01617   0.00999  -0.0074   1.0000   0.0985
  -9.750  -1.0930   0.01573   0.00958  -0.0058   1.0000   0.1019
  -9.500  -1.0712   0.01546   0.00927  -0.0046   1.0000   0.1049
  -9.250  -1.0487   0.01523   0.00898  -0.0034   1.0000   0.1078
  -9.000  -1.0273   0.01488   0.00858  -0.0020   1.0000   0.1106
  -8.750  -1.0065   0.01449   0.00822  -0.0006   1.0000   0.1141
  -8.500  -0.9841   0.01424   0.00796   0.0006   1.0000   0.1172
  -8.250  -0.9611   0.01405   0.00771   0.0018   1.0000   0.1202
  -8.000  -0.9385   0.01379   0.00740   0.0030   1.0000   0.1231
  -7.750  -0.9172   0.01341   0.00706   0.0044   1.0000   0.1267
  -7.500  -0.8944   0.01320   0.00685   0.0055   1.0000   0.1300
  -7.250  -0.8710   0.01303   0.00664   0.0066   1.0000   0.1332
  -7.000  -0.8473   0.01290   0.00645   0.0077   1.0000   0.1357
  -6.750  -0.8260   0.01248   0.00608   0.0091   1.0000   0.1398
  -6.500  -0.8030   0.01230   0.00591   0.0103   1.0000   0.1433
  -6.250  -0.7795   0.01215   0.00575   0.0114   1.0000   0.1467
  -6.000  -0.7558   0.01204   0.00557   0.0125   1.0000   0.1493
  -5.750  -0.7339   0.01170   0.00528   0.0138   1.0000   0.1533
  -5.500  -0.7110   0.01152   0.00513   0.0150   1.0000   0.1570
  -5.250  -0.6876   0.01139   0.00499   0.0161   1.0000   0.1605
  -5.000  -0.6641   0.01128   0.00485   0.0172   1.0000   0.1635
  -4.750  -0.6417   0.01106   0.00464   0.0185   1.0000   0.1671
  -4.500  -0.6192   0.01087   0.00451   0.0197   1.0000   0.1711
  -4.250  -0.5962   0.01077   0.00441   0.0209   1.0000   0.1748
  -4.000  -0.5563   0.01070   0.00433   0.0186   0.9970   0.1790
  -3.750  -0.5130   0.01049   0.00418   0.0154   0.9931   0.1847
  -3.500  -0.4733   0.01030   0.00404   0.0132   0.9881   0.1899
  -3.250  -0.4296   0.01018   0.00392   0.0101   0.9834   0.1947
  -3.000  -0.3912   0.00988   0.00369   0.0082   0.9763   0.2007
  -2.250  -0.2855   0.00911   0.00307   0.0047   0.9360   0.2186
  -2.000  -0.2216   0.00883   0.00280  -0.0024   0.9071   0.2281
  -1.750  -0.1572   0.00869   0.00247  -0.0097   0.8098   0.2402
  -1.500  -0.1356   0.00893   0.00236  -0.0078   0.7122   0.2480
  -1.250  -0.1155   0.00915   0.00230  -0.0059   0.6260   0.2577
  -1.000  -0.0942   0.00933   0.00224  -0.0043   0.5504   0.2689
  -0.750  -0.0713   0.00946   0.00220  -0.0030   0.4870   0.2825
  -0.500  -0.0478   0.00956   0.00217  -0.0019   0.4343   0.2998
  -0.250  -0.0239   0.00961   0.00215  -0.0010   0.3899   0.3226
   0.000   0.0000   0.00963   0.00214   0.0000   0.3524   0.3524
   0.250   0.0240   0.00961   0.00215   0.0010   0.3225   0.3897
   0.500   0.0478   0.00955   0.00217   0.0019   0.2999   0.4344
   0.750   0.0713   0.00946   0.00220   0.0030   0.2825   0.4870
   1.000   0.0942   0.00933   0.00224   0.0043   0.2690   0.5508
   1.250   0.1155   0.00915   0.00230   0.0059   0.2577   0.6258
   1.500   0.1356   0.00893   0.00236   0.0078   0.2479   0.7126
   1.750   0.1572   0.00869   0.00247   0.0097   0.2402   0.8095
   2.000   0.2214   0.00883   0.00280   0.0024   0.2281   0.9070
   2.250   0.2855   0.00911   0.00307  -0.0048   0.2186   0.9360
   3.000   0.3908   0.00988   0.00369  -0.0081   0.2005   0.9760
   3.250   0.4298   0.01018   0.00392  -0.0102   0.1947   0.9834
   3.500   0.4732   0.01030   0.00404  -0.0132   0.1899   0.9881
   3.750   0.5134   0.01049   0.00418  -0.0155   0.1847   0.9932
   4.000   0.5566   0.01070   0.00433  -0.0186   0.1789   0.9970
   4.250   0.5962   0.01077   0.00441  -0.0209   0.1749   1.0000
   4.500   0.6192   0.01088   0.00451  -0.0197   0.1712   1.0000
   4.750   0.6417   0.01106   0.00464  -0.0185   0.1671   1.0000
   5.000   0.6641   0.01128   0.00485  -0.0172   0.1635   1.0000
   5.250   0.6876   0.01139   0.00498  -0.0161   0.1605   1.0000
   5.500   0.7110   0.01152   0.00513  -0.0150   0.1570   1.0000
   5.750   0.7339   0.01170   0.00528  -0.0138   0.1533   1.0000
   6.000   0.7558   0.01203   0.00557  -0.0125   0.1493   1.0000
   6.250   0.7795   0.01215   0.00574  -0.0114   0.1467   1.0000
   6.500   0.8030   0.01230   0.00592  -0.0103   0.1433   1.0000
   6.750   0.8261   0.01248   0.00608  -0.0091   0.1398   1.0000
   7.000   0.8473   0.01290   0.00645  -0.0077   0.1357   1.0000
   7.250   0.8710   0.01303   0.00664  -0.0066   0.1332   1.0000
   7.500   0.8944   0.01319   0.00684  -0.0055   0.1300   1.0000
   7.750   0.9172   0.01341   0.00706  -0.0044   0.1267   1.0000
   8.000   0.9385   0.01379   0.00740  -0.0030   0.1231   1.0000
   8.250   0.9611   0.01405   0.00771  -0.0018   0.1202   1.0000
   8.500   0.9841   0.01424   0.00796  -0.0006   0.1172   1.0000
   8.750   1.0066   0.01449   0.00823   0.0006   0.1142   1.0000
   9.000   1.0274   0.01487   0.00858   0.0020   0.1107   1.0000
   9.250   1.0487   0.01523   0.00898   0.0034   0.1078   1.0000
   9.500   1.0712   0.01547   0.00928   0.0046   0.1050   1.0000
   9.750   1.0930   0.01573   0.00958   0.0058   0.1019   1.0000
  10.000   1.1128   0.01617   0.00999   0.0074   0.0985   1.0000
  10.250   1.1334   0.01655   0.01042   0.0088   0.0956   1.0000
  10.500   1.1555   0.01678   0.01071   0.0100   0.0924   1.0000
  10.750   1.1760   0.01711   0.01105   0.0113   0.0892   1.0000
  11.000   1.1930   0.01773   0.01164   0.0132   0.0857   1.0000
  11.250   1.2142   0.01801   0.01202   0.0145   0.0835   1.0000
  11.500   1.2344   0.01834   0.01241   0.0159   0.0806   1.0000
  11.750   1.2524   0.01882   0.01289   0.0176   0.0779   1.0000
  12.000   1.2674   0.01950   0.01359   0.0197   0.0750   1.0000
  12.250   1.2869   0.01986   0.01405   0.0211   0.0728   1.0000
  12.500   1.3049   0.02029   0.01453   0.0228   0.0702   1.0000
  12.750   1.3197   0.02089   0.01514   0.0248   0.0677   1.0000
  13.000   1.3321   0.02162   0.01591   0.0271   0.0652   1.0000
  13.250   1.3486   0.02209   0.01648   0.0289   0.0631   1.0000
  13.500   1.3626   0.02266   0.01711   0.0309   0.0607   1.0000
  13.750   1.3706   0.02344   0.01790   0.0337   0.0585   1.0000
  14.000   1.3742   0.02426   0.01878   0.0373   0.0566   1.0000
  14.250   1.3843   0.02487   0.01949   0.0397   0.0546   1.0000
  14.500   1.3912   0.02569   0.02036   0.0423   0.0526   1.0000
  14.750   1.3934   0.02683   0.02154   0.0450   0.0507   1.0000
  15.000   1.3929   0.02825   0.02304   0.0475   0.0490   1.0000
  15.250   1.3986   0.02946   0.02438   0.0491   0.0474   1.0000
  15.500   1.3996   0.03115   0.02616   0.0503   0.0456   1.0000
  15.750   1.3948   0.03362   0.02869   0.0508   0.0441   1.0000
  16.000   1.3826   0.03738   0.03257   0.0499   0.0430   1.0000
  16.250   1.3743   0.04145   0.03679   0.0478   0.0418   1.0000
  16.500   1.3601   0.04691   0.04243   0.0445   0.0410   1.0000
  16.750   1.3383   0.05379   0.04948   0.0401   0.0405   1.0000
  17.000   1.3080   0.06184   0.05770   0.0354   0.0402   1.0000
  17.250   1.2742   0.07023   0.06623   0.0308   0.0399   1.0000
  17.500   1.2411   0.07838   0.07451   0.0265   0.0398   1.0000
  17.750   1.2117   0.08601   0.08225   0.0225   0.0395   1.0000
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