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E387 (e387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.51 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e387-il-1000000-n5.txt
Download as CSV file: xf-e387-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E387                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2638   0.09155   0.08951  -0.0308   0.8191   0.0065
  -9.250  -0.3617   0.09497   0.09335  -0.0271   0.9841   0.0048
  -9.000  -0.3276   0.08831   0.08661  -0.0387   0.9443   0.0046
  -8.750  -0.3114   0.08330   0.08134  -0.0448   0.8731   0.0045
  -8.500  -0.3089   0.08099   0.07885  -0.0451   0.8287   0.0044
  -8.250  -0.3120   0.07698   0.07475  -0.0464   0.8012   0.0044
  -8.000  -0.3122   0.07381   0.07151  -0.0476   0.7804   0.0043
  -7.750  -0.3184   0.07001   0.06768  -0.0488   0.7627   0.0043
  -7.500  -0.3197   0.06605   0.06368  -0.0520   0.7482   0.0043
  -7.250  -0.3204   0.05922   0.05680  -0.0590   0.7357   0.0044
  -7.000  -0.3129   0.05281   0.05030  -0.0656   0.7248   0.0043
  -6.750  -0.3321   0.02422   0.02067  -0.0793   0.7204   0.0047
  -6.500  -0.3129   0.02010   0.01598  -0.0797   0.7111   0.0048
  -6.250  -0.2894   0.01807   0.01359  -0.0798   0.7023   0.0048
  -6.000  -0.2645   0.01670   0.01192  -0.0797   0.6937   0.0049
  -5.750  -0.2388   0.01553   0.01050  -0.0796   0.6855   0.0049
  -5.500  -0.2133   0.01421   0.00889  -0.0795   0.6780   0.0051
  -5.250  -0.1878   0.01283   0.00726  -0.0794   0.6705   0.0053
  -5.000  -0.1611   0.01219   0.00649  -0.0794   0.6637   0.0055
  -4.750  -0.1340   0.01156   0.00573  -0.0793   0.6572   0.0056
  -4.250  -0.0796   0.01048   0.00442  -0.0791   0.6447   0.0058
  -4.000  -0.0522   0.01005   0.00389  -0.0790   0.6384   0.0060
  -3.750  -0.0246   0.00967   0.00343  -0.0789   0.6330   0.0062
  -3.500   0.0032   0.00934   0.00303  -0.0789   0.6270   0.0066
  -3.000   0.0590   0.00884   0.00240  -0.0788   0.6163   0.0073
  -2.750   0.0870   0.00866   0.00217  -0.0788   0.6107   0.0076
  -2.500   0.1149   0.00842   0.00185  -0.0788   0.6056   0.0081
  -2.250   0.1430   0.00823   0.00162  -0.0788   0.6008   0.0089
  -2.000   0.1711   0.00810   0.00145  -0.0788   0.5954   0.0100
  -1.750   0.1992   0.00800   0.00130  -0.0788   0.5906   0.0109
  -1.500   0.2275   0.00788   0.00117  -0.0789   0.5856   0.0144
  -1.250   0.2554   0.00767   0.00106  -0.0789   0.5805   0.0454
  -1.000   0.2834   0.00753   0.00099  -0.0790   0.5758   0.0770
  -0.750   0.3113   0.00731   0.00094  -0.0791   0.5709   0.1348
  -0.500   0.3393   0.00716   0.00091  -0.0792   0.5660   0.1845
  -0.250   0.3671   0.00698   0.00089  -0.0793   0.5614   0.2512
   0.000   0.3949   0.00674   0.00089  -0.0794   0.5564   0.3406
   0.250   0.4224   0.00649   0.00091  -0.0795   0.5515   0.4443
   0.500   0.4500   0.00633   0.00093  -0.0796   0.5469   0.5224
   0.750   0.4776   0.00616   0.00096  -0.0796   0.5417   0.6008
   1.000   0.5042   0.00593   0.00101  -0.0794   0.5365   0.7111
   1.250   0.5288   0.00565   0.00107  -0.0786   0.5315   0.8335
   1.500   0.5554   0.00541   0.00110  -0.0780   0.5249   0.9643
   1.750   0.5895   0.00547   0.00112  -0.0794   0.5176   1.0000
   2.000   0.6173   0.00555   0.00116  -0.0794   0.5093   1.0000
   2.250   0.6450   0.00563   0.00120  -0.0794   0.5008   1.0000
   2.750   0.7003   0.00582   0.00132  -0.0793   0.4820   1.0000
   3.000   0.7279   0.00593   0.00139  -0.0793   0.4725   1.0000
   3.250   0.7553   0.00606   0.00147  -0.0792   0.4615   1.0000
   3.500   0.7827   0.00619   0.00157  -0.0792   0.4492   1.0000
   3.750   0.8097   0.00635   0.00168  -0.0791   0.4331   1.0000
   4.000   0.8359   0.00661   0.00181  -0.0789   0.4020   1.0000
   4.250   0.8614   0.00696   0.00200  -0.0787   0.3651   1.0000
   4.500   0.8867   0.00735   0.00223  -0.0784   0.3263   1.0000
   4.750   0.9077   0.00826   0.00269  -0.0776   0.2387   1.0000
   5.000   0.9298   0.00903   0.00313  -0.0769   0.1723   1.0000
   5.250   0.9531   0.00963   0.00351  -0.0764   0.1295   1.0000
   5.500   0.9763   0.01022   0.00391  -0.0759   0.0907   1.0000
   5.750   0.9996   0.01079   0.00431  -0.0754   0.0587   1.0000
   6.000   1.0221   0.01142   0.00478  -0.0747   0.0290   1.0000
   6.250   1.0447   0.01203   0.00528  -0.0741   0.0098   1.0000
   6.500   1.0695   0.01237   0.00564  -0.0737   0.0085   1.0000
   6.750   1.0940   0.01272   0.00600  -0.0733   0.0076   1.0000
   7.000   1.1181   0.01311   0.00643  -0.0728   0.0070   1.0000
   7.250   1.1422   0.01346   0.00682  -0.0723   0.0068   1.0000
   7.500   1.1659   0.01386   0.00726  -0.0718   0.0065   1.0000
   7.750   1.1892   0.01427   0.00771  -0.0712   0.0061   1.0000
   8.000   1.2118   0.01473   0.00821  -0.0706   0.0059   1.0000
   8.250   1.2338   0.01522   0.00875  -0.0698   0.0056   1.0000
   8.500   1.2553   0.01574   0.00931  -0.0690   0.0054   1.0000
   8.750   1.2760   0.01631   0.00994  -0.0681   0.0053   1.0000
   9.000   1.2956   0.01694   0.01062  -0.0671   0.0051   1.0000
   9.250   1.3138   0.01764   0.01138  -0.0658   0.0049   1.0000
   9.500   1.3299   0.01847   0.01228  -0.0643   0.0048   1.0000
   9.750   1.3430   0.01945   0.01335  -0.0624   0.0046   1.0000
  10.000   1.3531   0.02048   0.01448  -0.0600   0.0045   1.0000
  10.250   1.3643   0.02121   0.01528  -0.0577   0.0045   1.0000
  10.500   1.3736   0.02205   0.01618  -0.0553   0.0044   1.0000
  10.750   1.3824   0.02296   0.01718  -0.0530   0.0044   1.0000
  11.000   1.3902   0.02402   0.01831  -0.0508   0.0043   1.0000
  11.250   1.3969   0.02524   0.01962  -0.0488   0.0043   1.0000
  11.500   1.4048   0.02646   0.02092  -0.0471   0.0042   1.0000
  11.750   1.4087   0.02810   0.02266  -0.0454   0.0041   1.0000
  12.000   1.4141   0.02972   0.02437  -0.0440   0.0041   1.0000
  12.250   1.4212   0.03128   0.02602  -0.0429   0.0039   1.0000
  12.500   1.4248   0.03324   0.02809  -0.0418   0.0039   1.0000
  12.750   1.4309   0.03506   0.02999  -0.0410   0.0037   1.0000
  13.000   1.4331   0.03732   0.03236  -0.0402   0.0037   1.0000
  13.250   1.4370   0.03950   0.03464  -0.0397   0.0036   1.0000
  13.500   1.4377   0.04210   0.03735  -0.0392   0.0036   1.0000
  13.750   1.4390   0.04472   0.04007  -0.0389   0.0035   1.0000
  14.000   1.4394   0.04752   0.04297  -0.0388   0.0035   1.0000
  14.250   1.4382   0.05057   0.04614  -0.0388   0.0034   1.0000
  14.500   1.4353   0.05393   0.04962  -0.0390   0.0034   1.0000
  14.750   1.4341   0.05721   0.05301  -0.0394   0.0034   1.0000
  15.000   1.4307   0.06087   0.05680  -0.0400   0.0034   1.0000
  15.250   1.4271   0.06474   0.06079  -0.0409   0.0033   1.0000
  15.500   1.4226   0.06891   0.06507  -0.0420   0.0033   1.0000
  15.750   1.4179   0.07323   0.06951  -0.0433   0.0033   1.0000
  16.000   1.4116   0.07796   0.07437  -0.0449   0.0032   1.0000
  16.250   1.4031   0.08325   0.07980  -0.0469   0.0032   1.0000
  16.500   1.3956   0.08854   0.08521  -0.0491   0.0032   1.0000
  16.750   1.3862   0.09435   0.09116  -0.0516   0.0032   1.0000
  17.000   1.3770   0.10036   0.09729  -0.0544   0.0032   1.0000
  17.250   1.3654   0.10698   0.10405  -0.0577   0.0031   1.0000
  17.500   1.3537   0.11381   0.11101  -0.0612   0.0031   1.0000
  17.750   1.3432   0.12064   0.11796  -0.0649   0.0031   1.0000
  18.000   1.3296   0.12832   0.12578  -0.0691   0.0031   1.0000
  18.250   1.3170   0.13598   0.13357  -0.0735   0.0031   1.0000
  18.500   1.3023   0.14436   0.14208  -0.0785   0.0031   1.0000
  18.750   1.2887   0.15274   0.15059  -0.0836   0.0031   1.0000
  19.000   1.2736   0.16176   0.15975  -0.0892   0.0031   1.0000
  19.250   1.2588   0.17102   0.16914  -0.0950   0.0031   1.0000
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