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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 50,000
Max Cl/Cd: 37.55 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e392-il-50000-n5.txt
Download as CSV file: xf-e392-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3373   0.09414   0.08759  -0.0431   1.0000   0.0490
  -8.000  -0.3364   0.09119   0.08470  -0.0426   1.0000   0.0485
  -7.750  -0.3398   0.08847   0.08211  -0.0421   1.0000   0.0480
  -7.500  -0.3456   0.08593   0.07970  -0.0414   1.0000   0.0475
  -7.250  -0.3517   0.08324   0.07715  -0.0412   1.0000   0.0469
  -7.000  -0.3589   0.08063   0.07467  -0.0410   1.0000   0.0462
  -6.750  -0.3686   0.07800   0.07217  -0.0409   1.0000   0.0459
  -6.500  -0.3787   0.07549   0.06975  -0.0406   1.0000   0.0454
  -6.250  -0.3790   0.07174   0.06603  -0.0432   0.9970   0.0449
  -6.000  -0.3514   0.06487   0.05898  -0.0531   0.9851   0.0441
  -5.750  -0.3235   0.05827   0.05211  -0.0618   0.9734   0.0436
  -5.500  -0.2946   0.05201   0.04544  -0.0692   0.9619   0.0426
  -5.250  -0.2632   0.04632   0.03922  -0.0752   0.9517   0.0420
  -5.000  -0.2268   0.04128   0.03353  -0.0805   0.9437   0.0420
  -4.750  -0.1946   0.03751   0.02915  -0.0834   0.9338   0.0425
  -4.500  -0.1580   0.03423   0.02523  -0.0863   0.9262   0.0442
  -4.250  -0.1217   0.03169   0.02195  -0.0883   0.9181   0.0485
  -4.000  -0.0873   0.02965   0.01965  -0.0900   0.9103   0.0531
  -3.750  -0.0518   0.02786   0.01752  -0.0912   0.9029   0.0589
  -3.500  -0.0201   0.02656   0.01605  -0.0920   0.8945   0.0702
  -3.250   0.0147   0.02521   0.01454  -0.0932   0.8873   0.0913
  -3.000   0.0448   0.02410   0.01344  -0.0938   0.8782   0.1291
  -2.750   0.0802   0.02274   0.01238  -0.0957   0.8717   0.2058
  -2.500   0.1070   0.02162   0.01194  -0.0961   0.8623   0.3468
  -2.250   0.1342   0.02083   0.01178  -0.0954   0.8555   0.5385
  -2.000   0.1525   0.02053   0.01177  -0.0926   0.8458   0.6665
  -1.750   0.1709   0.02023   0.01164  -0.0892   0.8377   0.7809
  -1.500   0.2127   0.01980   0.01115  -0.0904   0.8309   0.9483
  -1.250   0.2485   0.01985   0.01078  -0.0924   0.8227   1.0000
  -1.000   0.2789   0.01999   0.01056  -0.0932   0.8147   1.0000
  -0.750   0.3062   0.02024   0.01051  -0.0936   0.8060   1.0000
  -0.500   0.3375   0.02039   0.01037  -0.0943   0.7991   1.0000
  -0.250   0.3630   0.02071   0.01046  -0.0943   0.7902   1.0000
   0.000   0.3943   0.02087   0.01040  -0.0949   0.7839   1.0000
   0.250   0.4187   0.02125   0.01061  -0.0947   0.7749   1.0000
   0.500   0.4497   0.02143   0.01060  -0.0952   0.7689   1.0000
   0.750   0.4731   0.02187   0.01093  -0.0949   0.7600   1.0000
   1.000   0.5038   0.02206   0.01098  -0.0953   0.7542   1.0000
   1.250   0.5265   0.02256   0.01141  -0.0949   0.7453   1.0000
   1.500   0.5568   0.02278   0.01152  -0.0952   0.7397   1.0000
   1.750   0.5790   0.02332   0.01203  -0.0948   0.7308   1.0000
   2.000   0.6089   0.02356   0.01222  -0.0950   0.7252   1.0000
   2.250   0.6306   0.02416   0.01281  -0.0945   0.7164   1.0000
   2.500   0.6602   0.02440   0.01303  -0.0946   0.7107   1.0000
   2.750   0.6814   0.02505   0.01370  -0.0940   0.7019   1.0000
   3.000   0.7108   0.02530   0.01398  -0.0941   0.6962   1.0000
   3.250   0.7313   0.02601   0.01473  -0.0935   0.6872   1.0000
   3.500   0.7609   0.02625   0.01500  -0.0935   0.6814   1.0000
   3.750   0.7806   0.02700   0.01584  -0.0928   0.6721   1.0000
   4.000   0.8110   0.02718   0.01610  -0.0928   0.6663   1.0000
   4.250   0.8296   0.02799   0.01703  -0.0919   0.6563   1.0000
   4.500   0.8566   0.02832   0.01745  -0.0916   0.6491   1.0000
   4.750   0.8793   0.02886   0.01815  -0.0910   0.6398   1.0000
   5.000   0.9009   0.02946   0.01888  -0.0901   0.6300   1.0000
   5.250   0.9318   0.02945   0.01899  -0.0899   0.6226   1.0000
   5.500   0.9508   0.03011   0.01982  -0.0888   0.6109   1.0000
   5.750   0.9723   0.03058   0.02050  -0.0877   0.5997   1.0000
   6.000   0.9976   0.03076   0.02086  -0.0869   0.5889   1.0000
   6.250   1.0271   0.03057   0.02084  -0.0862   0.5781   1.0000
   6.500   1.0501   0.03073   0.02119  -0.0849   0.5647   1.0000
   6.750   1.0732   0.03078   0.02149  -0.0836   0.5502   1.0000
   7.000   1.0939   0.03089   0.02182  -0.0820   0.5339   1.0000
   7.250   1.1114   0.03113   0.02230  -0.0801   0.5155   1.0000
   7.500   1.1323   0.03103   0.02241  -0.0782   0.4959   1.0000
   7.750   1.1501   0.03107   0.02266  -0.0761   0.4736   1.0000
   8.000   1.1671   0.03108   0.02287  -0.0738   0.4477   1.0000
   8.250   1.1791   0.03142   0.02337  -0.0711   0.4169   1.0000
   8.500   1.1900   0.03182   0.02381  -0.0683   0.3800   1.0000
   8.750   1.1962   0.03257   0.02447  -0.0651   0.3368   1.0000
   9.000   1.1965   0.03384   0.02551  -0.0617   0.2931   1.0000
   9.250   1.1929   0.03574   0.02715  -0.0585   0.2528   1.0000
   9.500   1.1871   0.03813   0.02934  -0.0559   0.2171   1.0000
   9.750   1.1793   0.04096   0.03193  -0.0539   0.1846   1.0000
  10.000   1.1711   0.04410   0.03485  -0.0524   0.1556   1.0000
  10.250   1.1641   0.04740   0.03798  -0.0514   0.1296   1.0000
  10.500   1.1590   0.05073   0.04124  -0.0507   0.1080   1.0000
  10.750   1.1544   0.05416   0.04459  -0.0501   0.0919   1.0000
  11.000   1.1515   0.05753   0.04793  -0.0495   0.0795   1.0000
  11.250   1.1505   0.06080   0.05122  -0.0489   0.0697   1.0000
  11.500   1.1500   0.06405   0.05446  -0.0484   0.0630   1.0000
  11.750   1.1548   0.06683   0.05739  -0.0475   0.0574   1.0000
  12.000   1.1591   0.06963   0.06018  -0.0467   0.0536   1.0000
  12.250   1.1709   0.07198   0.06284  -0.0455   0.0494   1.0000
  12.500   1.1779   0.07474   0.06579  -0.0449   0.0460   1.0000
  12.750   1.1857   0.07739   0.06843  -0.0443   0.0432   1.0000
  13.000   1.1943   0.08058   0.07204  -0.0437   0.0413   1.0000
  13.250   1.1990   0.08439   0.07622  -0.0435   0.0400   1.0000
  13.500   1.1976   0.08887   0.08104  -0.0440   0.0392   1.0000
  13.750   1.1914   0.09400   0.08648  -0.0451   0.0387   1.0000
  14.000   1.1809   0.09978   0.09255  -0.0470   0.0383   1.0000
  14.250   1.1668   0.10630   0.09935  -0.0498   0.0382   1.0000
  14.500   1.1496   0.11372   0.10702  -0.0536   0.0383   1.0000
  14.750   1.1297   0.12221   0.11573  -0.0584   0.0386   1.0000
  15.000   1.1079   0.13196   0.12568  -0.0645   0.0390   1.0000
  15.250   1.0851   0.14314   0.13695  -0.0716   0.0396   1.0000
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