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EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 556 AIRFOIL (e556-il)
Reynolds number: 50,000
Max Cl/Cd: 32.53 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e556-il-50000-n5.txt
Download as CSV file: xf-e556-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 556 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4604   0.10811   0.10064  -0.0548   1.0000   0.0459
 -12.250  -0.4796   0.09995   0.09250  -0.0586   1.0000   0.0451
 -12.000  -0.5078   0.09095   0.08347  -0.0632   1.0000   0.0438
 -11.750  -0.5377   0.08300   0.07541  -0.0673   1.0000   0.0431
 -11.500  -0.5666   0.07615   0.06841  -0.0704   1.0000   0.0423
 -11.250  -0.5889   0.07088   0.06297  -0.0722   1.0000   0.0418
 -11.000  -0.6023   0.06717   0.05917  -0.0726   1.0000   0.0424
 -10.750  -0.6144   0.06390   0.05582  -0.0725   1.0000   0.0431
 -10.500  -0.6258   0.06087   0.05266  -0.0718   1.0000   0.0436
 -10.250  -0.6368   0.05823   0.04991  -0.0706   1.0000   0.0444
 -10.000  -0.6470   0.05588   0.04743  -0.0687   1.0000   0.0452
  -9.750  -0.6563   0.05378   0.04519  -0.0663   1.0000   0.0460
  -9.500  -0.6606   0.05166   0.04288  -0.0640   1.0000   0.0472
  -9.250  -0.6579   0.04977   0.04082  -0.0617   1.0000   0.0489
  -9.000  -0.6533   0.04842   0.03953  -0.0594   1.0000   0.0514
  -8.750  -0.6501   0.04706   0.03810  -0.0571   1.0000   0.0542
  -8.500  -0.6436   0.04573   0.03655  -0.0543   1.0000   0.0579
  -8.250  -0.6387   0.04460   0.03551  -0.0516   1.0000   0.0611
  -8.000  -0.6368   0.04339   0.03431  -0.0491   1.0000   0.0653
  -7.750  -0.6327   0.04224   0.03303  -0.0464   1.0000   0.0706
  -7.500  -0.6317   0.04095   0.03186  -0.0443   1.0000   0.0756
  -7.250  -0.6276   0.03972   0.03053  -0.0422   1.0000   0.0830
  -7.000  -0.6248   0.03823   0.02916  -0.0407   1.0000   0.0903
  -6.750  -0.6055   0.03636   0.02732  -0.0425   0.9955   0.1055
  -6.500  -0.5782   0.03380   0.02495  -0.0468   0.9878   0.1333
  -6.250  -0.5497   0.03050   0.02225  -0.0526   0.9805   0.1968
  -5.750  -0.4828   0.03180   0.02432  -0.0551   0.9641   0.3998
  -5.500  -0.4507   0.03308   0.02535  -0.0551   0.9553   0.4313
  -5.250  -0.4143   0.03408   0.02605  -0.0562   0.9482   0.4582
  -5.000  -0.3883   0.03510   0.02690  -0.0546   0.9386   0.4753
  -4.750  -0.3579   0.03595   0.02759  -0.0539   0.9310   0.4918
  -4.500  -0.3282   0.03622   0.02765  -0.0541   0.9225   0.5067
  -4.250  -0.3006   0.03664   0.02795  -0.0530   0.9143   0.5153
  -4.000  -0.2678   0.03619   0.02725  -0.0548   0.9066   0.5252
  -3.750  -0.2388   0.03592   0.02680  -0.0555   0.8981   0.5321
  -3.500  -0.2029   0.03519   0.02581  -0.0585   0.8907   0.5401
  -3.250  -0.1751   0.03495   0.02543  -0.0587   0.8820   0.5448
  -3.000  -0.1381   0.03430   0.02455  -0.0617   0.8749   0.5517
  -2.750  -0.1085   0.03386   0.02395  -0.0629   0.8661   0.5569
  -2.500  -0.0740   0.03351   0.02347  -0.0644   0.8591   0.5613
  -2.250  -0.0435   0.03307   0.02286  -0.0660   0.8501   0.5669
  -2.000  -0.0056   0.03253   0.02215  -0.0688   0.8434   0.5723
  -1.750   0.0214   0.03235   0.02190  -0.0689   0.8342   0.5762
  -1.500   0.0585   0.03193   0.02136  -0.0711   0.8275   0.5811
  -1.250   0.0909   0.03156   0.02083  -0.0732   0.8185   0.5871
  -1.000   0.1255   0.03129   0.02052  -0.0743   0.8116   0.5909
  -0.750   0.1528   0.03116   0.02033  -0.0747   0.8021   0.5953
  -0.500   0.1932   0.03075   0.01980  -0.0775   0.7956   0.6010
  -0.250   0.2194   0.03066   0.01968  -0.0777   0.7856   0.6053
   0.000   0.2563   0.03037   0.01936  -0.0792   0.7791   0.6099
   0.250   0.2827   0.03033   0.01927  -0.0797   0.7688   0.6153
   0.500   0.3230   0.02996   0.01884  -0.0820   0.7626   0.6206
   0.750   0.3450   0.03005   0.01895  -0.0813   0.7516   0.6249
   1.000   0.3863   0.02968   0.01854  -0.0836   0.7459   0.6309
   1.250   0.4097   0.02980   0.01866  -0.0835   0.7344   0.6363
   1.500   0.4400   0.02971   0.01859  -0.0839   0.7262   0.6411
   1.750   0.4712   0.02964   0.01853  -0.0847   0.7171   0.6471
   2.000   0.4985   0.02972   0.01862  -0.0849   0.7072   0.6530
   2.250   0.5327   0.02953   0.01847  -0.0858   0.6997   0.6587
   2.500   0.5573   0.02975   0.01871  -0.0858   0.6888   0.6654
   2.750   0.5951   0.02945   0.01844  -0.0871   0.6823   0.6714
   3.000   0.6149   0.02979   0.01887  -0.0862   0.6706   0.6780
   3.250   0.6432   0.02989   0.01902  -0.0864   0.6612   0.6850
   3.500   0.6738   0.02984   0.01906  -0.0867   0.6526   0.6920
   3.750   0.6969   0.03016   0.01944  -0.0864   0.6417   0.6998
   4.000   0.7335   0.02987   0.01922  -0.0873   0.6346   0.7077
   4.250   0.7523   0.03033   0.01980  -0.0863   0.6227   0.7161
   4.500   0.7753   0.03056   0.02015  -0.0855   0.6125   0.7244
   4.750   0.8088   0.03042   0.02009  -0.0861   0.6040   0.7340
   5.000   0.8271   0.03087   0.02067  -0.0849   0.5923   0.7442
   5.250   0.8511   0.03102   0.02096  -0.0841   0.5823   0.7545
   5.500   0.8808   0.03095   0.02100  -0.0840   0.5727   0.7665
   5.750   0.8977   0.03140   0.02161  -0.0825   0.5608   0.7792
   6.000   0.9198   0.03158   0.02195  -0.0815   0.5500   0.7937
   6.250   0.9492   0.03135   0.02185  -0.0810   0.5403   0.8104
   6.500   0.9606   0.03180   0.02250  -0.0785   0.5279   0.8291
   6.750   0.9758   0.03205   0.02295  -0.0763   0.5163   0.8534
   7.000   0.9970   0.03190   0.02296  -0.0747   0.5056   0.8914
   7.250   1.0247   0.03183   0.02302  -0.0747   0.4933   1.0000
   7.500   1.0482   0.03244   0.02370  -0.0748   0.4793   1.0000
   7.750   1.0705   0.03303   0.02438  -0.0746   0.4653   1.0000
   8.000   1.0915   0.03359   0.02500  -0.0740   0.4513   1.0000
   8.250   1.1107   0.03414   0.02560  -0.0730   0.4371   1.0000
   8.500   1.1286   0.03470   0.02622  -0.0718   0.4227   1.0000
   8.750   1.1450   0.03532   0.02691  -0.0704   0.4080   1.0000
   9.000   1.1595   0.03601   0.02765  -0.0688   0.3929   1.0000
   9.250   1.1724   0.03680   0.02849  -0.0670   0.3778   1.0000
   9.500   1.1832   0.03769   0.02944  -0.0651   0.3624   1.0000
   9.750   1.1925   0.03870   0.03050  -0.0632   0.3468   1.0000
  10.000   1.2003   0.03985   0.03172  -0.0612   0.3312   1.0000
  10.250   1.2067   0.04114   0.03305  -0.0593   0.3156   1.0000
  10.500   1.2118   0.04258   0.03454  -0.0575   0.3000   1.0000
  10.750   1.2159   0.04419   0.03619  -0.0558   0.2847   1.0000
  11.000   1.2192   0.04595   0.03798  -0.0542   0.2698   1.0000
  11.250   1.2217   0.04786   0.03992  -0.0528   0.2552   1.0000
  11.500   1.2240   0.04991   0.04199  -0.0516   0.2412   1.0000
  11.750   1.2257   0.05209   0.04420  -0.0505   0.2278   1.0000
  12.000   1.2278   0.05433   0.04642  -0.0495   0.2150   1.0000
  12.250   1.2271   0.05700   0.04917  -0.0488   0.2028   1.0000
  12.500   1.2253   0.05995   0.05220  -0.0483   0.1911   1.0000
  12.750   1.2247   0.06285   0.05514  -0.0479   0.1804   1.0000
  13.000   1.2260   0.06553   0.05780  -0.0476   0.1704   1.0000
  13.250   1.2230   0.06893   0.06131  -0.0476   0.1607   1.0000
  13.500   1.2208   0.07237   0.06486  -0.0478   0.1520   1.0000
  13.750   1.2238   0.07500   0.06742  -0.0477   0.1435   1.0000
  14.000   1.2156   0.07957   0.07225  -0.0486   0.1359   1.0000
  14.250   1.2184   0.08241   0.07505  -0.0488   0.1286   1.0000
  14.500   1.2096   0.08737   0.08028  -0.0501   0.1223   1.0000
  14.750   1.2143   0.08995   0.08276  -0.0503   0.1156   1.0000
  15.000   1.2010   0.09596   0.08910  -0.0524   0.1106   1.0000
  15.250   1.1998   0.09979   0.09300  -0.0535   0.1052   1.0000
  15.500   1.1955   0.10437   0.09768  -0.0551   0.1006   1.0000
  15.750   1.1783   0.11161   0.10521  -0.0585   0.0971   1.0000
  16.000   1.1724   0.11670   0.11041  -0.0607   0.0930   1.0000
  16.250   1.1747   0.12016   0.11387  -0.0619   0.0889   1.0000
  16.500   1.1423   0.13149   0.12551  -0.0685   0.0876   1.0000
  16.750   1.0884   0.14931   0.14355  -0.0795   0.0871   1.0000
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