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EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 642 AIRFOIL (e642-il)
Reynolds number: 500,000
Max Cl/Cd: 92.6 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e642-il-500000-n5.txt
Download as CSV file: xf-e642-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 642 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4971   0.04891   0.04497  -0.0955   0.7255   0.0086
 -11.250  -0.5185   0.04497   0.04084  -0.0950   0.7218   0.0087
 -10.750  -0.5557   0.03869   0.03410  -0.0901   0.7145   0.0087
 -10.500  -0.5654   0.03655   0.03174  -0.0869   0.7115   0.0087
 -10.250  -0.5769   0.03424   0.02919  -0.0828   0.7087   0.0087
 -10.000  -0.5868   0.03200   0.02670  -0.0785   0.7060   0.0088
  -9.750  -0.5866   0.02980   0.02423  -0.0754   0.7034   0.0088
  -9.500  -0.5791   0.02811   0.02234  -0.0732   0.7009   0.0089
  -9.250  -0.5675   0.02674   0.02079  -0.0713   0.6985   0.0091
  -9.000  -0.5527   0.02571   0.01963  -0.0699   0.6964   0.0093
  -8.500  -0.5188   0.02358   0.01717  -0.0674   0.6924   0.0096
  -8.250  -0.4998   0.02250   0.01592  -0.0663   0.6901   0.0097
  -8.000  -0.4796   0.02144   0.01471  -0.0654   0.6879   0.0099
  -7.750  -0.4585   0.02039   0.01349  -0.0646   0.6860   0.0100
  -7.500  -0.4363   0.01947   0.01242  -0.0638   0.6841   0.0101
  -7.250  -0.4135   0.01863   0.01144  -0.0632   0.6824   0.0103
  -7.000  -0.3903   0.01787   0.01056  -0.0626   0.6808   0.0105
  -6.750  -0.3669   0.01717   0.00974  -0.0620   0.6792   0.0107
  -6.500  -0.3432   0.01655   0.00905  -0.0615   0.6777   0.0109
  -6.250  -0.3193   0.01599   0.00841  -0.0610   0.6762   0.0112
  -6.000  -0.2955   0.01547   0.00783  -0.0604   0.6744   0.0114
  -5.750  -0.2715   0.01501   0.00733  -0.0599   0.6725   0.0116
  -5.500  -0.2478   0.01455   0.00682  -0.0593   0.6708   0.0118
  -5.250  -0.2252   0.01397   0.00620  -0.0586   0.6692   0.0122
  -5.000  -0.2017   0.01354   0.00574  -0.0580   0.6677   0.0125
  -4.750  -0.1773   0.01321   0.00538  -0.0576   0.6662   0.0130
  -4.500  -0.1524   0.01293   0.00507  -0.0572   0.6647   0.0138
  -4.250  -0.1274   0.01267   0.00475  -0.0568   0.6631   0.0144
  -4.000  -0.1020   0.01241   0.00447  -0.0565   0.6616   0.0150
  -3.750  -0.0765   0.01217   0.00421  -0.0562   0.6601   0.0155
  -3.500  -0.0511   0.01191   0.00393  -0.0559   0.6584   0.0167
  -3.250  -0.0253   0.01171   0.00371  -0.0556   0.6567   0.0182
  -3.000   0.0008   0.01153   0.00352  -0.0554   0.6549   0.0206
  -2.750   0.0257   0.01124   0.00333  -0.0551   0.6531   0.0400
  -2.500   0.0492   0.01085   0.00315  -0.0546   0.6514   0.0959
  -2.250   0.0726   0.01045   0.00301  -0.0540   0.6498   0.1638
  -2.000   0.0963   0.01011   0.00288  -0.0536   0.6481   0.2348
  -1.750   0.1167   0.00949   0.00273  -0.0527   0.6464   0.3655
  -1.500   0.1352   0.00875   0.00257  -0.0515   0.6445   0.5198
  -1.250   0.1471   0.00806   0.00292  -0.0480   0.6425   0.7717
  -1.000   0.1743   0.00828   0.00311  -0.0477   0.6404   0.8130
  -0.750   0.2018   0.00845   0.00326  -0.0475   0.6384   0.8232
  -0.500   0.2287   0.00866   0.00344  -0.0471   0.6365   0.8340
  -0.250   0.2561   0.00883   0.00355  -0.0469   0.6346   0.8439
   0.000   0.2825   0.00903   0.00375  -0.0463   0.6327   0.8493
   0.250   0.3095   0.00917   0.00387  -0.0461   0.6307   0.8554
   0.500   0.3368   0.00924   0.00393  -0.0460   0.6284   0.8603
   0.750   0.3637   0.00930   0.00400  -0.0458   0.6258   0.8627
   1.000   0.3914   0.00932   0.00400  -0.0458   0.6232   0.8643
   1.250   0.4195   0.00932   0.00398  -0.0461   0.6206   0.8656
   1.500   0.4479   0.00933   0.00394  -0.0464   0.6181   0.8666
   1.750   0.4762   0.00933   0.00393  -0.0467   0.6154   0.8677
   2.000   0.5043   0.00932   0.00394  -0.0469   0.6120   0.8688
   2.250   0.5325   0.00930   0.00392  -0.0473   0.6084   0.8696
   2.500   0.5608   0.00929   0.00390  -0.0476   0.6048   0.8706
   2.750   0.5891   0.00930   0.00387  -0.0479   0.6013   0.8716
   3.000   0.6172   0.00928   0.00390  -0.0483   0.5966   0.8723
   3.250   0.6454   0.00928   0.00390  -0.0486   0.5918   0.8729
   3.500   0.6734   0.00928   0.00388  -0.0489   0.5873   0.8736
   3.750   0.7015   0.00929   0.00392  -0.0492   0.5816   0.8742
   4.000   0.7284   0.00928   0.00393  -0.0492   0.5752   0.8748
   4.250   0.7553   0.00930   0.00397  -0.0493   0.5682   0.8755
   4.500   0.7818   0.00931   0.00399  -0.0492   0.5593   0.8760
   4.750   0.8083   0.00934   0.00403  -0.0492   0.5490   0.8765
   5.000   0.8341   0.00940   0.00409  -0.0491   0.5378   0.8771
   5.250   0.8591   0.00949   0.00416  -0.0487   0.5239   0.8777
   5.500   0.8831   0.00961   0.00425  -0.0483   0.5082   0.8783
   5.750   0.9060   0.00979   0.00438  -0.0476   0.4906   0.8790
   6.000   0.9279   0.01002   0.00456  -0.0468   0.4722   0.8797
   6.250   0.9485   0.01029   0.00477  -0.0458   0.4522   0.8806
   6.500   0.9687   0.01058   0.00501  -0.0447   0.4324   0.8817
   6.750   0.9875   0.01091   0.00528  -0.0434   0.4120   0.8827
   7.000   1.0050   0.01128   0.00558  -0.0419   0.3903   0.8837
   7.250   1.0211   0.01168   0.00591  -0.0402   0.3685   0.8847
   7.500   1.0338   0.01213   0.00628  -0.0378   0.3453   0.8858
   7.750   1.0388   0.01270   0.00672  -0.0341   0.3160   0.8872
   8.000   1.0431   0.01342   0.00731  -0.0306   0.2863   0.8885
   8.250   1.0459   0.01424   0.00798  -0.0269   0.2567   0.8899
   8.500   1.0477   0.01514   0.00876  -0.0234   0.2281   0.8914
   8.750   1.0521   0.01604   0.00957  -0.0204   0.2047   0.8928
   9.000   1.0591   0.01692   0.01040  -0.0181   0.1880   0.8943
   9.250   1.0663   0.01787   0.01130  -0.0160   0.1719   0.8960
   9.500   1.0731   0.01891   0.01230  -0.0140   0.1545   0.8978
   9.750   1.0806   0.02000   0.01334  -0.0122   0.1387   0.8993
  10.000   1.0873   0.02119   0.01447  -0.0105   0.1222   0.9008
  10.250   1.0923   0.02254   0.01573  -0.0088   0.1044   0.9023
  10.500   1.0993   0.02382   0.01695  -0.0073   0.0895   0.9037
  10.750   1.1060   0.02509   0.01818  -0.0058   0.0763   0.9052
  11.000   1.1123   0.02642   0.01949  -0.0044   0.0638   0.9067
  11.250   1.1163   0.02795   0.02095  -0.0029   0.0498   0.9084
  11.500   1.1229   0.02934   0.02233  -0.0016   0.0404   0.9101
  11.750   1.1276   0.03091   0.02387  -0.0004   0.0307   0.9120
  12.000   1.1343   0.03238   0.02534   0.0007   0.0240   0.9139
  12.250   1.1390   0.03406   0.02700   0.0018   0.0158   0.9158
  12.500   1.1441   0.03575   0.02871   0.0027   0.0117   0.9178
  12.750   1.1510   0.03732   0.03032   0.0036   0.0101   0.9198
  13.000   1.1581   0.03892   0.03199   0.0043   0.0093   0.9223
  13.250   1.1669   0.04040   0.03355   0.0049   0.0088   0.9252
  13.500   1.1744   0.04203   0.03527   0.0055   0.0083   0.9287
  14.000   1.1866   0.04576   0.03917   0.0064   0.0074   0.9372
  14.250   1.1929   0.04781   0.04132   0.0065   0.0072   0.9428
  14.500   1.2005   0.04991   0.04353   0.0063   0.0071   0.9500
  15.000   1.2147   0.05459   0.04843   0.0050   0.0067   1.0000
  15.250   1.2189   0.05703   0.05096   0.0048   0.0067   1.0000
  15.500   1.2223   0.05962   0.05364   0.0046   0.0065   1.0000
  15.750   1.2246   0.06239   0.05651   0.0043   0.0063   1.0000
  16.000   1.2268   0.06527   0.05948   0.0039   0.0062   1.0000
  16.250   1.2273   0.06841   0.06272   0.0033   0.0061   1.0000
  16.500   1.2277   0.07163   0.06605   0.0026   0.0060   1.0000
  16.750   1.2272   0.07505   0.06956   0.0018   0.0059   1.0000
  17.000   1.2250   0.07878   0.07339   0.0008   0.0058   1.0000
  17.250   1.2237   0.08247   0.07719  -0.0003   0.0058   1.0000
  17.500   1.2204   0.08653   0.08134  -0.0015   0.0057   1.0000
  17.750   1.2171   0.09064   0.08557  -0.0029   0.0057   1.0000
  18.000   1.2128   0.09501   0.09003  -0.0045   0.0056   1.0000
  18.250   1.2073   0.09965   0.09477  -0.0063   0.0054   1.0000
  18.500   1.2036   0.10409   0.09931  -0.0082   0.0054   1.0000
  18.750   1.1976   0.10893   0.10426  -0.0103   0.0054   1.0000
  19.000   1.1923   0.11372   0.10916  -0.0124   0.0053   1.0000
  19.250   1.1865   0.11867   0.11421  -0.0147   0.0053   1.0000
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