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EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 587 AIRFOIL (e587-il)
Reynolds number: 100,000
Max Cl/Cd: 44.79 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e587-il-100000.txt
Download as CSV file: xf-e587-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 587 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2988   0.12386   0.11954  -0.0588   0.9749   0.1017
  -9.750  -0.3100   0.11964   0.11537  -0.0669   0.9710   0.1077
  -9.500  -0.3477   0.11598   0.11181  -0.0737   0.9624   0.1086
  -9.250  -0.2890   0.11216   0.10791  -0.0678   0.9619   0.1130
  -9.000  -0.2773   0.10850   0.10424  -0.0710   0.9589   0.1186
  -8.750  -0.3175   0.10532   0.10117  -0.0756   0.9502   0.1229
  -8.500  -0.2987   0.10085   0.09670  -0.0758   0.9474   0.1264
  -8.250  -0.2759   0.09771   0.09353  -0.0774   0.9449   0.1322
  -8.000  -0.3087   0.09507   0.09098  -0.0776   0.9361   0.1367
  -7.750  -0.3674   0.09133   0.08729  -0.0815   0.9279   0.1382
  -7.500  -0.4196   0.08867   0.08447  -0.0832   0.9181   0.1389
  -7.250  -0.3436   0.08570   0.08172  -0.0781   0.9191   0.1470
  -7.000  -0.3741   0.08195   0.07794  -0.0808   0.9129   0.1512
  -6.000  -0.4159   0.05423   0.04741  -0.0856   0.8914   0.0584
  -5.750  -0.3914   0.05001   0.04316  -0.0868   0.8881   0.0555
  -5.500  -0.3552   0.04540   0.03745  -0.0890   0.8855   0.0501
  -5.250  -0.3278   0.04353   0.03515  -0.0893   0.8822   0.0497
  -5.000  -0.3163   0.04206   0.03361  -0.0876   0.8775   0.0510
  -4.750  -0.2901   0.04096   0.03244  -0.0879   0.8733   0.0545
  -4.500  -0.2538   0.03951   0.03063  -0.0891   0.8702   0.0574
  -4.250  -0.2149   0.03789   0.02898  -0.0908   0.8679   0.0613
  -4.000  -0.2141   0.03768   0.02877  -0.0870   0.8619   0.0654
  -3.750  -0.1892   0.03684   0.02799  -0.0869   0.8576   0.0756
  -3.500  -0.1551   0.03574   0.02705  -0.0881   0.8543   0.0976
  -3.250  -0.1106   0.03361   0.02583  -0.0923   0.8522   0.2112
  -3.000  -0.1135   0.03320   0.02746  -0.0874   0.8462   0.6149
  -2.750  -0.1043   0.03480   0.02898  -0.0820   0.8408   0.6705
  -2.500  -0.0880   0.03620   0.03029  -0.0772   0.8371   0.7047
  -2.250  -0.0891   0.03718   0.03122  -0.0716   0.8311   0.7242
  -2.000  -0.0811   0.03800   0.03195  -0.0672   0.8256   0.7460
  -1.750  -0.0684   0.03871   0.03258  -0.0625   0.8217   0.7656
  -1.500  -0.0648   0.03932   0.03312  -0.0578   0.8161   0.7821
  -1.250  -0.0606   0.03976   0.03350  -0.0534   0.8101   0.7979
  -1.000  -0.0494   0.04009   0.03375  -0.0487   0.8060   0.8185
  -0.750  -0.0480   0.04046   0.03407  -0.0435   0.8001   0.8394
  -0.500  -0.0500   0.04066   0.03423  -0.0380   0.7941   0.8581
  -0.250  -0.0327   0.04063   0.03409  -0.0352   0.7897   0.8745
   0.000  -0.0206   0.04085   0.03422  -0.0335   0.7833   0.8817
   0.250   0.0025   0.04116   0.03440  -0.0343   0.7770   0.8874
   0.500   0.0399   0.04119   0.03428  -0.0361   0.7728   0.8919
   0.750   0.0484   0.04164   0.03467  -0.0347   0.7648   0.8969
   1.000   0.0800   0.04191   0.03482  -0.0365   0.7592   0.9012
   1.250   0.1270   0.04199   0.03475  -0.0398   0.7556   0.9044
   1.500   0.1251   0.04262   0.03537  -0.0372   0.7457   0.9094
   1.750   0.1645   0.04275   0.03540  -0.0395   0.7411   0.9135
   2.000   0.1801   0.04347   0.03606  -0.0396   0.7327   0.9176
   2.250   0.2100   0.04363   0.03616  -0.0406   0.7267   0.9217
   2.500   0.2563   0.04358   0.03603  -0.0435   0.7234   0.9260
   2.750   0.2588   0.04458   0.03703  -0.0420   0.7123   0.9313
   3.000   0.3017   0.04452   0.03691  -0.0445   0.7084   0.9352
   3.250   0.3092   0.04546   0.03785  -0.0435   0.6979   0.9413
   3.500   0.3503   0.04539   0.03775  -0.0457   0.6932   0.9468
   3.750   0.3642   0.04631   0.03869  -0.0456   0.6835   0.9535
   4.000   0.4043   0.04635   0.03872  -0.0480   0.6781   0.9593
   4.250   0.4566   0.04603   0.03839  -0.0515   0.6753   0.9654
   4.500   0.4682   0.04738   0.03979  -0.0520   0.6628   0.9762
   4.750   0.5214   0.04682   0.03925  -0.0557   0.6598   1.0000
   5.000   0.5302   0.04831   0.04076  -0.0558   0.6473   1.0000
   5.250   0.5818   0.04778   0.04023  -0.0591   0.6444   1.0000
   5.500   0.5926   0.04932   0.04181  -0.0594   0.6319   1.0000
   5.750   0.6443   0.04861   0.04114  -0.0625   0.6290   1.0000
   6.000   0.6566   0.05015   0.04273  -0.0629   0.6165   1.0000
   6.250   0.7088   0.04920   0.04184  -0.0659   0.6136   1.0000
   6.500   0.7215   0.05078   0.04346  -0.0662   0.6009   1.0000
   6.750   0.7742   0.04956   0.04231  -0.0690   0.5982   1.0000
   7.000   0.7878   0.05108   0.04389  -0.0693   0.5855   1.0000
   7.250   0.8403   0.04963   0.04253  -0.0718   0.5828   1.0000
   7.500   0.8976   0.04762   0.04063  -0.0745   0.5814   1.0000
   7.750   0.9086   0.04917   0.04225  -0.0744   0.5677   1.0000
   8.000   0.9670   0.04669   0.03988  -0.0768   0.5664   1.0000
   8.250   1.0280   0.04366   0.03699  -0.0792   0.5657   1.0000
   8.750   1.0832   0.04324   0.03680  -0.0798   0.5460   1.0000
   9.000   1.1728   0.03787   0.03160  -0.0843   0.5474   1.0000
   9.250   1.2138   0.03649   0.03034  -0.0853   0.5373   1.0000
   9.500   1.2531   0.03529   0.02926  -0.0863   0.5260   1.0000
   9.750   1.3240   0.03219   0.02626  -0.0903   0.5149   1.0000
  10.000   1.3568   0.03156   0.02568  -0.0907   0.4988   1.0000
  10.250   1.3783   0.03159   0.02576  -0.0898   0.4810   1.0000
  10.500   1.3990   0.03170   0.02588  -0.0889   0.4619   1.0000
  10.750   1.4221   0.03175   0.02588  -0.0882   0.4416   1.0000
  11.000   1.4344   0.03244   0.02653  -0.0865   0.4212   1.0000
  11.250   1.4379   0.03365   0.02776  -0.0839   0.4009   1.0000
  11.500   1.4450   0.03474   0.02879  -0.0818   0.3802   1.0000
  11.750   1.4538   0.03583   0.02977  -0.0800   0.3596   1.0000
  12.000   1.4520   0.03760   0.03156  -0.0774   0.3401   1.0000
  12.250   1.4515   0.03939   0.03332  -0.0750   0.3208   1.0000
  12.500   1.4515   0.04122   0.03510  -0.0729   0.3019   1.0000
  12.750   1.4522   0.04310   0.03691  -0.0709   0.2834   1.0000
  13.000   1.4508   0.04523   0.03898  -0.0690   0.2655   1.0000
  13.250   1.4468   0.04766   0.04142  -0.0672   0.2485   1.0000
  13.500   1.4428   0.05020   0.04396  -0.0655   0.2318   1.0000
  13.750   1.4387   0.05288   0.04663  -0.0640   0.2156   1.0000
  14.000   1.4344   0.05572   0.04945  -0.0627   0.1999   1.0000
  14.250   1.4298   0.05869   0.05241  -0.0616   0.1849   1.0000
  14.500   1.4252   0.06180   0.05551  -0.0606   0.1705   1.0000
  14.750   1.4205   0.06505   0.05875  -0.0598   0.1568   1.0000
  15.000   1.4162   0.06838   0.06205  -0.0592   0.1437   1.0000
  15.250   1.4124   0.07175   0.06538  -0.0587   0.1314   1.0000
  15.500   1.4099   0.07506   0.06860  -0.0584   0.1195   1.0000
  15.750   1.4034   0.07901   0.07268  -0.0583   0.1095   1.0000
  16.000   1.3999   0.08272   0.07646  -0.0583   0.0998   1.0000
  16.250   1.3986   0.08615   0.07986  -0.0583   0.0911   1.0000
  16.500   1.4018   0.08899   0.08253  -0.0582   0.0822   1.0000
  16.750   1.3940   0.09356   0.08742  -0.0589   0.0765   1.0000
  17.000   1.3976   0.09645   0.09022  -0.0590   0.0698   1.0000
  17.250   1.3924   0.10073   0.09474  -0.0598   0.0650   1.0000
  17.500   1.3975   0.10349   0.09743  -0.0601   0.0595   1.0000
  17.750   1.3910   0.10808   0.10229  -0.0612   0.0559   1.0000
  18.000   1.4007   0.11019   0.10425  -0.0613   0.0511   1.0000
  18.250   1.3900   0.11552   0.10993  -0.0631   0.0488   1.0000
  18.500   1.3848   0.12002   0.11462  -0.0647   0.0463   1.0000
  18.750   1.3934   0.12233   0.11684  -0.0651   0.0429   1.0000
  19.000   1.3782   0.12859   0.12344  -0.0679   0.0419   1.0000
  19.250   1.3643   0.13480   0.12994  -0.0710   0.0407   1.0000
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