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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 50,000
Max Cl/Cd: 39.85 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e214-il-50000-n5.txt
Download as CSV file: xf-e214-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E214  (11.1%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3572   0.10580   0.09903  -0.0404   1.0000   0.0614
  -8.500  -0.3599   0.10282   0.09613  -0.0397   1.0000   0.0595
  -8.250  -0.3661   0.09992   0.09333  -0.0391   1.0000   0.0585
  -8.000  -0.3743   0.09722   0.09074  -0.0384   1.0000   0.0581
  -7.500  -0.4241   0.08888   0.08270  -0.0417   1.0000   0.0513
  -7.250  -0.4296   0.08545   0.07934  -0.0420   1.0000   0.0511
  -7.000  -0.4347   0.08165   0.07559  -0.0431   1.0000   0.0509
  -6.750  -0.4406   0.07722   0.07118  -0.0452   1.0000   0.0508
  -6.500  -0.4442   0.07273   0.06664  -0.0473   1.0000   0.0508
  -6.250  -0.4440   0.06831   0.06212  -0.0495   1.0000   0.0507
  -6.000  -0.4400   0.06341   0.05702  -0.0524   1.0000   0.0508
  -5.750  -0.4264   0.05842   0.05172  -0.0562   0.9988   0.0508
  -5.500  -0.3947   0.05264   0.04546  -0.0629   0.9933   0.0507
  -5.250  -0.3606   0.04746   0.03968  -0.0687   0.9879   0.0507
  -5.000  -0.3226   0.04301   0.03450  -0.0738   0.9836   0.0511
  -4.750  -0.2884   0.03957   0.03053  -0.0772   0.9782   0.0522
  -4.500  -0.2533   0.03759   0.02835  -0.0802   0.9730   0.0562
  -4.250  -0.2179   0.03543   0.02570  -0.0826   0.9675   0.0596
  -4.000  -0.1815   0.03340   0.02316  -0.0846   0.9621   0.0618
  -3.750  -0.1458   0.03186   0.02116  -0.0861   0.9569   0.0644
  -3.500  -0.1146   0.03057   0.01984  -0.0870   0.9503   0.0685
  -3.250  -0.0785   0.02969   0.01867  -0.0887   0.9448   0.0780
  -3.000  -0.0488   0.02878   0.01776  -0.0895   0.9371   0.0891
  -2.750  -0.0094   0.02772   0.01670  -0.0921   0.9322   0.1124
  -2.500   0.0231   0.02652   0.01590  -0.0941   0.9244   0.1879
  -2.250   0.0601   0.02507   0.01582  -0.0969   0.9195   0.4374
  -2.000   0.0838   0.02505   0.01604  -0.0955   0.9104   0.5812
  -1.750   0.1132   0.02507   0.01606  -0.0947   0.9039   0.6648
  -1.500   0.1324   0.02508   0.01606  -0.0924   0.8938   0.7174
  -1.250   0.1541   0.02501   0.01595  -0.0904   0.8851   0.7654
  -1.000   0.1776   0.02484   0.01573  -0.0887   0.8772   0.8131
  -0.750   0.1948   0.02466   0.01552  -0.0861   0.8672   0.8613
  -0.500   0.2350   0.02428   0.01504  -0.0879   0.8614   0.9430
  -0.250   0.2689   0.02431   0.01484  -0.0901   0.8506   1.0000
   0.000   0.3046   0.02447   0.01473  -0.0924   0.8421   1.0000
   0.250   0.3434   0.02455   0.01457  -0.0949   0.8349   1.0000
   0.500   0.3744   0.02478   0.01461  -0.0962   0.8253   1.0000
   0.750   0.4151   0.02476   0.01440  -0.0987   0.8194   1.0000
   1.000   0.4430   0.02503   0.01454  -0.0992   0.8089   1.0000
   1.250   0.4783   0.02511   0.01449  -0.1007   0.8014   1.0000
   1.500   0.5111   0.02524   0.01453  -0.1018   0.7928   1.0000
   1.750   0.5405   0.02547   0.01468  -0.1023   0.7831   1.0000
   2.000   0.5796   0.02542   0.01455  -0.1042   0.7767   1.0000
   2.250   0.6059   0.02573   0.01483  -0.1042   0.7659   1.0000
   2.500   0.6401   0.02581   0.01488  -0.1053   0.7578   1.0000
   2.750   0.6733   0.02591   0.01496  -0.1062   0.7491   1.0000
   3.000   0.7007   0.02619   0.01527  -0.1062   0.7385   1.0000
   3.250   0.7407   0.02603   0.01510  -0.1079   0.7319   1.0000
   3.500   0.7660   0.02637   0.01548  -0.1076   0.7204   1.0000
   3.750   0.7931   0.02665   0.01583  -0.1075   0.7094   1.0000
   4.000   0.8265   0.02669   0.01592  -0.1081   0.7002   1.0000
   4.250   0.8586   0.02677   0.01606  -0.1086   0.6901   1.0000
   4.500   0.8840   0.02711   0.01647  -0.1081   0.6779   1.0000
   4.750   0.9113   0.02736   0.01685  -0.1079   0.6661   1.0000
   5.000   0.9409   0.02751   0.01709  -0.1079   0.6545   1.0000
   5.250   0.9727   0.02756   0.01723  -0.1081   0.6429   1.0000
   5.500   1.0038   0.02761   0.01743  -0.1082   0.6304   1.0000
   5.750   1.0295   0.02785   0.01779  -0.1075   0.6163   1.0000
   6.000   1.0554   0.02807   0.01813  -0.1069   0.6016   1.0000
   6.250   1.0803   0.02830   0.01848  -0.1060   0.5862   1.0000
   6.500   1.1007   0.02868   0.01901  -0.1045   0.5692   1.0000
   6.750   1.1216   0.02902   0.01953  -0.1031   0.5514   1.0000
   7.000   1.1438   0.02925   0.01989  -0.1017   0.5329   1.0000
   7.250   1.1677   0.02938   0.02011  -0.1005   0.5136   1.0000
   7.500   1.1820   0.02992   0.02080  -0.0981   0.4922   1.0000
   7.750   1.2022   0.03017   0.02111  -0.0963   0.4703   1.0000
   8.000   1.2138   0.03080   0.02192  -0.0936   0.4464   1.0000
   8.250   1.2259   0.03136   0.02255  -0.0909   0.4216   1.0000
   8.500   1.2363   0.03202   0.02323  -0.0880   0.3955   1.0000
   8.750   1.2444   0.03286   0.02408  -0.0850   0.3682   1.0000
   9.000   1.2504   0.03390   0.02510  -0.0819   0.3402   1.0000
   9.250   1.2544   0.03515   0.02634  -0.0788   0.3119   1.0000
   9.500   1.2570   0.03663   0.02778  -0.0759   0.2840   1.0000
   9.750   1.2581   0.03835   0.02949  -0.0731   0.2570   1.0000
  10.000   1.2585   0.04028   0.03138  -0.0705   0.2319   1.0000
  10.250   1.2580   0.04242   0.03345  -0.0682   0.2095   1.0000
  10.500   1.2573   0.04475   0.03576  -0.0661   0.1885   1.0000
  10.750   1.2562   0.04725   0.03821  -0.0642   0.1710   1.0000
  11.000   1.2554   0.04988   0.04083  -0.0627   0.1544   1.0000
  11.250   1.2551   0.05262   0.04360  -0.0613   0.1397   1.0000
  11.500   1.2548   0.05546   0.04645  -0.0601   0.1270   1.0000
  11.750   1.2541   0.05841   0.04941  -0.0592   0.1159   1.0000
  12.000   1.2556   0.06137   0.05250  -0.0583   0.1050   1.0000
  12.250   1.2564   0.06448   0.05574  -0.0576   0.0954   1.0000
  12.500   1.2563   0.06769   0.05905  -0.0570   0.0873   1.0000
  12.750   1.2566   0.07099   0.06248  -0.0566   0.0797   1.0000
  13.000   1.2565   0.07451   0.06618  -0.0564   0.0728   1.0000
  13.250   1.2551   0.07807   0.06983  -0.0564   0.0670   1.0000
  13.500   1.2541   0.08197   0.07394  -0.0564   0.0617   1.0000
  13.750   1.2498   0.08620   0.07838  -0.0571   0.0570   1.0000
  14.000   1.2493   0.08983   0.08195  -0.0574   0.0531   1.0000
  14.250   1.2418   0.09515   0.08771  -0.0587   0.0501   1.0000
  14.500   1.2340   0.10045   0.09327  -0.0604   0.0475   1.0000
  14.750   1.2275   0.10545   0.09842  -0.0622   0.0452   1.0000
  15.000   1.2277   0.10921   0.10211  -0.0631   0.0427   1.0000
  15.250   1.2142   0.11620   0.10945  -0.0664   0.0420   1.0000
  15.500   1.1991   0.12380   0.11735  -0.0704   0.0415   1.0000
  15.750   1.1825   0.13215   0.12596  -0.0752   0.0413   1.0000
  16.000   1.1647   0.14140   0.13542  -0.0810   0.0414   1.0000
  16.250   1.1460   0.15157   0.14576  -0.0874   0.0417   1.0000
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