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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 500,000
Max Cl/Cd: 79.13 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e224-il-500000-n5.txt
Download as CSV file: xf-e224-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7133   0.05439   0.05182  -0.0496   1.0000   0.0044
 -11.000  -0.7484   0.04396   0.04113  -0.0591   1.0000   0.0042
 -10.750  -0.7632   0.04013   0.03715  -0.0608   1.0000   0.0043
 -10.500  -0.7855   0.03718   0.03402  -0.0583   1.0000   0.0043
 -10.250  -0.7945   0.03439   0.03100  -0.0562   1.0000   0.0043
 -10.000  -0.7981   0.03178   0.02814  -0.0539   1.0000   0.0043
  -9.750  -0.7979   0.02930   0.02538  -0.0515   1.0000   0.0043
  -9.500  -0.7924   0.02730   0.02314  -0.0493   1.0000   0.0045
  -9.250  -0.7819   0.02589   0.02155  -0.0474   1.0000   0.0046
  -9.000  -0.7730   0.02408   0.01949  -0.0452   1.0000   0.0047
  -8.750  -0.7456   0.02280   0.01801  -0.0463   0.9980   0.0050
  -8.500  -0.7167   0.02139   0.01637  -0.0476   0.9954   0.0052
  -8.250  -0.6885   0.01993   0.01467  -0.0486   0.9928   0.0054
  -8.000  -0.6603   0.01870   0.01325  -0.0495   0.9895   0.0055
  -7.750  -0.6308   0.01750   0.01187  -0.0505   0.9864   0.0056
  -7.500  -0.6015   0.01588   0.01006  -0.0517   0.9837   0.0059
  -7.250  -0.5735   0.01491   0.00899  -0.0523   0.9798   0.0063
  -7.000  -0.5442   0.01419   0.00817  -0.0530   0.9757   0.0067
  -6.750  -0.5126   0.01356   0.00745  -0.0541   0.9727   0.0071
  -6.500  -0.4798   0.01295   0.00675  -0.0554   0.9703   0.0077
  -6.250  -0.4518   0.01244   0.00616  -0.0556   0.9646   0.0083
  -6.000  -0.4212   0.01197   0.00562  -0.0563   0.9598   0.0089
  -5.750  -0.3887   0.01143   0.00505  -0.0575   0.9560   0.0113
  -5.500  -0.3604   0.01104   0.00459  -0.0577   0.9486   0.0138
  -5.250  -0.3286   0.01061   0.00414  -0.0586   0.9432   0.0191
  -5.000  -0.2994   0.01024   0.00377  -0.0590   0.9356   0.0268
  -4.750  -0.2688   0.00986   0.00343  -0.0597   0.9287   0.0397
  -4.500  -0.2408   0.00948   0.00313  -0.0598   0.9195   0.0623
  -4.250  -0.2125   0.00908   0.00284  -0.0601   0.9106   0.0950
  -4.000  -0.1846   0.00877   0.00260  -0.0602   0.9005   0.1231
  -3.750  -0.1573   0.00850   0.00239  -0.0601   0.8894   0.1529
  -3.500  -0.1304   0.00822   0.00220  -0.0600   0.8777   0.1903
  -3.250  -0.1036   0.00794   0.00203  -0.0598   0.8657   0.2339
  -3.000  -0.0767   0.00775   0.00188  -0.0596   0.8534   0.2676
  -2.750  -0.0497   0.00758   0.00175  -0.0594   0.8408   0.2977
  -2.500  -0.0229   0.00742   0.00164  -0.0592   0.8281   0.3326
  -2.000   0.0307   0.00715   0.00146  -0.0587   0.8014   0.4015
  -1.750   0.0575   0.00704   0.00139  -0.0585   0.7874   0.4356
  -1.500   0.0844   0.00695   0.00133  -0.0582   0.7730   0.4678
  -1.250   0.1111   0.00687   0.00128  -0.0579   0.7583   0.4994
  -1.000   0.1379   0.00681   0.00125  -0.0576   0.7433   0.5301
  -0.750   0.1646   0.00676   0.00123  -0.0574   0.7279   0.5601
  -0.500   0.1913   0.00672   0.00122  -0.0570   0.7122   0.5902
  -0.250   0.2180   0.00670   0.00122  -0.0567   0.6959   0.6194
   0.000   0.2445   0.00668   0.00123  -0.0564   0.6789   0.6493
   0.250   0.2708   0.00668   0.00125  -0.0560   0.6614   0.6786
   0.500   0.2970   0.00670   0.00128  -0.0555   0.6436   0.7060
   0.750   0.3233   0.00672   0.00132  -0.0551   0.6257   0.7321
   1.000   0.3494   0.00676   0.00138  -0.0546   0.6070   0.7576
   1.250   0.3752   0.00681   0.00144  -0.0541   0.5881   0.7827
   1.500   0.4008   0.00687   0.00151  -0.0535   0.5688   0.8074
   1.750   0.4260   0.00694   0.00158  -0.0528   0.5480   0.8314
   2.000   0.4509   0.00704   0.00167  -0.0521   0.5272   0.8553
   2.250   0.4753   0.00713   0.00176  -0.0512   0.5061   0.8784
   2.500   0.4995   0.00725   0.00186  -0.0503   0.4849   0.9013
   2.750   0.5240   0.00738   0.00196  -0.0494   0.4621   0.9242
   3.000   0.5512   0.00753   0.00206  -0.0492   0.4381   0.9466
   3.250   0.5827   0.00774   0.00218  -0.0501   0.4107   0.9679
   3.500   0.6172   0.00797   0.00231  -0.0517   0.3834   0.9882
   3.750   0.6462   0.00822   0.00247  -0.0521   0.3575   1.0000
   4.000   0.6710   0.00848   0.00264  -0.0516   0.3317   1.0000
   4.250   0.6954   0.00879   0.00282  -0.0511   0.3027   1.0000
   4.500   0.7197   0.00913   0.00304  -0.0505   0.2709   1.0000
   4.750   0.7444   0.00947   0.00328  -0.0501   0.2444   1.0000
   5.000   0.7692   0.00978   0.00351  -0.0496   0.2212   1.0000
   5.250   0.7933   0.01018   0.00378  -0.0491   0.1924   1.0000
   5.500   0.8168   0.01064   0.00409  -0.0485   0.1602   1.0000
   5.750   0.8403   0.01111   0.00442  -0.0479   0.1315   1.0000
   6.250   0.8881   0.01196   0.00513  -0.0468   0.0920   1.0000
   6.500   0.9120   0.01238   0.00549  -0.0462   0.0770   1.0000
   6.750   0.9355   0.01283   0.00589  -0.0456   0.0627   1.0000
   7.000   0.9587   0.01331   0.00631  -0.0450   0.0496   1.0000
   7.250   0.9819   0.01378   0.00675  -0.0444   0.0397   1.0000
   7.500   1.0048   0.01427   0.00725  -0.0437   0.0311   1.0000
   7.750   1.0273   0.01480   0.00777  -0.0429   0.0246   1.0000
   8.000   1.0494   0.01534   0.00831  -0.0421   0.0206   1.0000
   8.250   1.0715   0.01589   0.00890  -0.0412   0.0179   1.0000
   8.500   1.0936   0.01639   0.00946  -0.0405   0.0163   1.0000
   8.750   1.1147   0.01698   0.01009  -0.0395   0.0144   1.0000
   9.000   1.1341   0.01772   0.01090  -0.0384   0.0130   1.0000
   9.250   1.1553   0.01824   0.01150  -0.0375   0.0122   1.0000
   9.500   1.1755   0.01882   0.01215  -0.0365   0.0113   1.0000
   9.750   1.1950   0.01944   0.01282  -0.0354   0.0103   1.0000
  10.000   1.2120   0.02024   0.01368  -0.0340   0.0093   1.0000
  10.250   1.2279   0.02109   0.01462  -0.0324   0.0087   1.0000
  10.500   1.2453   0.02175   0.01540  -0.0310   0.0081   1.0000
  10.750   1.2604   0.02249   0.01623  -0.0293   0.0074   1.0000
  11.000   1.2732   0.02326   0.01708  -0.0273   0.0069   1.0000
  11.250   1.2845   0.02410   0.01799  -0.0251   0.0064   1.0000
  11.500   1.2926   0.02517   0.01914  -0.0227   0.0060   1.0000
  11.750   1.2988   0.02636   0.02044  -0.0202   0.0057   1.0000
  12.000   1.3091   0.02732   0.02151  -0.0183   0.0053   1.0000
  12.250   1.3170   0.02847   0.02277  -0.0164   0.0049   1.0000
  12.500   1.3231   0.02980   0.02421  -0.0146   0.0047   1.0000
  12.750   1.3311   0.03104   0.02554  -0.0131   0.0044   1.0000
  13.000   1.3350   0.03268   0.02729  -0.0116   0.0042   1.0000
  13.250   1.3394   0.03437   0.02910  -0.0104   0.0040   1.0000
  13.500   1.3402   0.03648   0.03133  -0.0093   0.0039   1.0000
  13.750   1.3371   0.03914   0.03412  -0.0084   0.0037   1.0000
  14.000   1.3289   0.04254   0.03767  -0.0080   0.0036   1.0000
  14.250   1.3260   0.04561   0.04089  -0.0081   0.0035   1.0000
  14.500   1.3197   0.04931   0.04474  -0.0087   0.0035   1.0000
  14.750   1.3164   0.05287   0.04845  -0.0096   0.0034   1.0000
  15.000   1.3052   0.05773   0.05348  -0.0113   0.0034   1.0000
  15.250   1.2964   0.06255   0.05845  -0.0132   0.0033   1.0000
  15.500   1.2861   0.06790   0.06396  -0.0157   0.0033   1.0000
  15.750   1.2698   0.07455   0.07078  -0.0190   0.0033   1.0000
  16.000   1.2546   0.08140   0.07778  -0.0226   0.0032   1.0000
  16.250   1.2381   0.08877   0.08531  -0.0266   0.0033   1.0000
  16.500   1.2211   0.09657   0.09326  -0.0310   0.0033   1.0000
  16.750   1.2014   0.10518   0.10202  -0.0358   0.0033   1.0000
  17.000   1.1815   0.11411   0.11110  -0.0409   0.0033   1.0000
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