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

E387 (e387-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 50,000
Max Cl/Cd: 38.09 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e387-il-50000.txt
Download as CSV file: xf-e387-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3597   0.10815   0.10165  -0.0251   1.0000   0.1800
  -8.250  -0.3401   0.10322   0.09671  -0.0237   1.0000   0.1894
  -8.000  -0.3602   0.10361   0.09730  -0.0263   1.0000   0.1936
  -7.750  -0.3350   0.09782   0.09148  -0.0244   1.0000   0.2047
  -7.500  -0.3366   0.09525   0.08904  -0.0247   1.0000   0.2115
  -7.250  -0.3420   0.09367   0.08759  -0.0245   1.0000   0.2216
  -7.000  -0.3314   0.09002   0.08399  -0.0231   1.0000   0.2330
  -6.750  -0.3590   0.09043   0.08467  -0.0250   1.0000   0.2377
  -6.500  -0.3500   0.08692   0.08124  -0.0221   1.0000   0.2514
  -6.250  -0.3442   0.08381   0.07823  -0.0195   1.0000   0.2638
  -6.000  -0.3496   0.08169   0.07625  -0.0172   1.0000   0.2729
  -5.750  -0.3767   0.08196   0.07671  -0.0160   1.0000   0.2813
  -5.500  -0.3759   0.07930   0.07414  -0.0112   1.0000   0.2920
  -5.250  -0.3905   0.07800   0.07296  -0.0085   1.0000   0.3010
  -5.000  -0.4052   0.07689   0.07196  -0.0070   1.0000   0.3133
  -4.750  -0.4127   0.07527   0.07041  -0.0049   1.0000   0.3277
  -4.500  -0.4156   0.07313   0.06834  -0.0018   1.0000   0.3438
  -4.250  -0.4172   0.07105   0.06632   0.0015   1.0000   0.3616
  -3.250  -0.2637   0.04490   0.03770  -0.0490   1.0000   0.1350
  -3.000  -0.2328   0.04086   0.03305  -0.0512   1.0000   0.1201
  -2.750  -0.2078   0.03811   0.03000  -0.0521   1.0000   0.1164
  -2.500  -0.1761   0.03570   0.02699  -0.0539   0.9984   0.1167
  -2.250  -0.1293   0.03333   0.02385  -0.0576   0.9914   0.1195
  -2.000  -0.0838   0.03132   0.02139  -0.0609   0.9844   0.1250
  -1.750  -0.0452   0.03007   0.01992  -0.0632   0.9763   0.1455
  -1.500  -0.0042   0.02876   0.01856  -0.0654   0.9694   0.1963
  -1.250   0.0357   0.02665   0.01743  -0.0675   0.9628   0.3778
  -1.000   0.0715   0.02441   0.01664  -0.0671   0.9556   1.0000
  -0.750   0.1059   0.02511   0.01674  -0.0693   0.9465   1.0000
  -0.500   0.1390   0.02585   0.01698  -0.0713   0.9374   1.0000
  -0.250   0.1790   0.02669   0.01741  -0.0744   0.9290   1.0000
   0.000   0.2033   0.02739   0.01783  -0.0749   0.9199   1.0000
   0.250   0.2377   0.02822   0.01836  -0.0770   0.9115   1.0000
   0.500   0.2656   0.02902   0.01893  -0.0781   0.9029   1.0000
   0.750   0.2924   0.02987   0.01960  -0.0790   0.8944   1.0000
   1.000   0.3260   0.03074   0.02030  -0.0810   0.8862   1.0000
   1.250   0.3456   0.03164   0.02106  -0.0808   0.8777   1.0000
   1.500   0.3827   0.03259   0.02187  -0.0832   0.8699   1.0000
   1.750   0.3973   0.03355   0.02276  -0.0823   0.8612   1.0000
   2.000   0.4269   0.03456   0.02368  -0.0835   0.8533   1.0000
   2.250   0.4480   0.03559   0.02466  -0.0836   0.8448   1.0000
   2.500   0.4704   0.03669   0.02572  -0.0839   0.8365   1.0000
   2.750   0.5001   0.03775   0.02676  -0.0851   0.8280   1.0000
   3.000   0.5142   0.03896   0.02795  -0.0843   0.8191   1.0000
   3.250   0.5457   0.04008   0.02909  -0.0856   0.8104   1.0000
   3.500   0.5620   0.04133   0.03035  -0.0851   0.8009   1.0000
   3.750   0.5806   0.04263   0.03168  -0.0849   0.7914   1.0000
   4.000   0.6122   0.04377   0.03288  -0.0861   0.7813   1.0000
   4.250   0.6314   0.04505   0.03425  -0.0858   0.7705   1.0000
   4.500   0.6463   0.04648   0.03573  -0.0852   0.7593   1.0000
   4.750   0.6677   0.04781   0.03715  -0.0851   0.7475   1.0000
   5.000   0.6924   0.04906   0.03850  -0.0853   0.7349   1.0000
   5.250   0.7178   0.05026   0.03982  -0.0854   0.7214   1.0000
   5.500   0.7418   0.05147   0.04121  -0.0852   0.7071   1.0000
   5.750   0.7633   0.05271   0.04259  -0.0847   0.6918   1.0000
   6.000   0.7843   0.05393   0.04396  -0.0841   0.6757   1.0000
   6.250   0.8083   0.05498   0.04518  -0.0836   0.6585   1.0000
   6.500   0.8439   0.05531   0.04581  -0.0833   0.6403   1.0000
   6.750   0.8790   0.05544   0.04620  -0.0826   0.6214   1.0000
   7.000   0.8940   0.05651   0.04746  -0.0808   0.6005   1.0000
   7.250   0.9692   0.05280   0.04433  -0.0799   0.5791   1.0000
   7.500   0.9983   0.05187   0.04372  -0.0773   0.5549   1.0000
   7.750   1.0647   0.04629   0.03872  -0.0736   0.5283   1.0000
   8.000   1.1443   0.03776   0.03073  -0.0689   0.4900   1.0000
   8.250   1.1832   0.03265   0.02578  -0.0634   0.4305   1.0000
   8.500   1.1895   0.03123   0.02392  -0.0572   0.3477   1.0000
   8.750   1.1787   0.03292   0.02472  -0.0517   0.2706   1.0000
   9.000   1.1651   0.03579   0.02686  -0.0472   0.2136   1.0000
   9.250   1.1541   0.03891   0.02948  -0.0433   0.1693   1.0000
   9.500   1.1619   0.04233   0.03243  -0.0407   0.1291   1.0000
   9.750   1.1976   0.04575   0.03563  -0.0405   0.1029   1.0000
  10.000   1.2400   0.04967   0.03961  -0.0412   0.0912   1.0000
  10.250   1.2607   0.05349   0.04402  -0.0401   0.0873   1.0000
  10.500   1.2758   0.05740   0.04833  -0.0389   0.0847   1.0000
  10.750   1.2915   0.06142   0.05254  -0.0380   0.0818   1.0000
  11.000   1.2994   0.06627   0.05759  -0.0371   0.0798   1.0000
  11.250   1.2909   0.07008   0.06185  -0.0347   0.0794   1.0000
  11.500   1.2789   0.07396   0.06609  -0.0324   0.0793   1.0000
  11.750   1.2637   0.07791   0.07033  -0.0304   0.0793   1.0000
  12.000   1.2474   0.08225   0.07490  -0.0291   0.0795   1.0000
  12.250   1.2312   0.08701   0.07987  -0.0287   0.0798   1.0000
  12.500   1.1514   0.09461   0.08807  -0.0326   0.0861   1.0000
  12.750   1.1200   0.10257   0.09619  -0.0365   0.0885   1.0000
  13.000   1.0946   0.11081   0.10450  -0.0408   0.0903   1.0000
  13.250   1.0774   0.11878   0.11252  -0.0447   0.0917   1.0000
  13.500   1.0697   0.12604   0.11980  -0.0476   0.0926   1.0000
  13.750   0.7837   0.15007   0.14405  -0.0629   0.1388   1.0000
  14.000   0.7856   0.15567   0.14967  -0.0645   0.1437   1.0000
<< Back to E387 (e387-il)

Polar data table (+)

Polar graphs


<< Back to E387 (e387-il)