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EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 556 AIRFOIL (e556-il)
Reynolds number: 200,000
Max Cl/Cd: 70.21 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e556-il-200000-n5.txt
Download as CSV file: xf-e556-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.6014   0.10523   0.10095  -0.0517   1.0000   0.0095
 -14.750  -0.6301   0.09505   0.09058  -0.0572   1.0000   0.0094
 -14.500  -0.6534   0.08682   0.08217  -0.0615   1.0000   0.0094
 -14.250  -0.6701   0.08037   0.07556  -0.0647   1.0000   0.0092
 -14.000  -0.6844   0.07474   0.06976  -0.0673   1.0000   0.0094
 -13.750  -0.6962   0.06984   0.06471  -0.0693   1.0000   0.0094
 -13.500  -0.7046   0.06574   0.06045  -0.0707   1.0000   0.0093
 -13.250  -0.7118   0.06205   0.05663  -0.0718   1.0000   0.0094
 -13.000  -0.7196   0.05850   0.05293  -0.0725   1.0000   0.0096
 -12.750  -0.7247   0.05546   0.04975  -0.0727   1.0000   0.0097
 -12.500  -0.7295   0.05257   0.04673  -0.0727   1.0000   0.0099
 -12.250  -0.7313   0.05020   0.04425  -0.0723   1.0000   0.0100
 -12.000  -0.7331   0.04795   0.04191  -0.0717   1.0000   0.0100
 -11.750  -0.7352   0.04580   0.03963  -0.0708   1.0000   0.0103
 -11.500  -0.7368   0.04389   0.03764  -0.0696   1.0000   0.0105
 -11.250  -0.7399   0.04207   0.03580  -0.0683   1.0000   0.0106
 -11.000  -0.7446   0.04035   0.03407  -0.0666   1.0000   0.0109
 -10.750  -0.7503   0.03884   0.03254  -0.0646   1.0000   0.0112
 -10.500  -0.7591   0.03740   0.03107  -0.0618   1.0000   0.0113
 -10.250  -0.7422   0.03567   0.02926  -0.0640   0.9965   0.0121
 -10.000  -0.7214   0.03388   0.02734  -0.0666   0.9913   0.0127
  -9.750  -0.7006   0.03212   0.02544  -0.0691   0.9852   0.0133
  -9.500  -0.6821   0.03008   0.02335  -0.0717   0.9771   0.0140
  -9.250  -0.6589   0.02822   0.02143  -0.0747   0.9698   0.0147
  -9.000  -0.6323   0.02640   0.01950  -0.0781   0.9632   0.0159
  -8.750  -0.6088   0.02487   0.01783  -0.0800   0.9555   0.0170
  -8.500  -0.5796   0.02346   0.01638  -0.0828   0.9502   0.0192
  -8.250  -0.5534   0.02226   0.01509  -0.0845   0.9435   0.0219
  -8.000  -0.5240   0.02112   0.01389  -0.0865   0.9378   0.0257
  -7.750  -0.4906   0.01991   0.01263  -0.0893   0.9343   0.0310
  -7.500  -0.4647   0.01898   0.01168  -0.0903   0.9262   0.0377
  -7.000  -0.3963   0.01703   0.00979  -0.0953   0.9174   0.0665
  -6.750  -0.3665   0.01611   0.00896  -0.0969   0.9098   0.0926
  -6.500  -0.3291   0.01500   0.00802  -0.1003   0.9055   0.1384
  -6.250  -0.2944   0.01362   0.00701  -0.1035   0.8994   0.2233
  -6.000  -0.2585   0.01279   0.00662  -0.1063   0.8929   0.3303
  -5.750  -0.2180   0.01264   0.00646  -0.1090   0.8883   0.3705
  -5.500  -0.1853   0.01261   0.00634  -0.1099   0.8796   0.3930
  -5.250  -0.1460   0.01259   0.00617  -0.1122   0.8734   0.4100
  -5.000  -0.1133   0.01261   0.00613  -0.1131   0.8643   0.4206
  -4.750  -0.0758   0.01263   0.00605  -0.1149   0.8570   0.4319
  -4.500  -0.0446   0.01277   0.00610  -0.1154   0.8469   0.4451
  -4.250  -0.0106   0.01283   0.00606  -0.1165   0.8382   0.4541
  -4.000   0.0215   0.01273   0.00579  -0.1174   0.8283   0.4582
  -3.750   0.0521   0.01265   0.00565  -0.1179   0.8184   0.4608
  -3.250   0.1131   0.01253   0.00534  -0.1189   0.7984   0.4671
  -3.000   0.1432   0.01248   0.00515  -0.1193   0.7886   0.4706
  -2.750   0.1735   0.01242   0.00495  -0.1198   0.7786   0.4738
  -2.500   0.2015   0.01238   0.00488  -0.1198   0.7681   0.4761
  -2.250   0.2304   0.01236   0.00480  -0.1200   0.7582   0.4789
  -2.000   0.2589   0.01235   0.00471  -0.1200   0.7480   0.4821
  -1.750   0.2871   0.01234   0.00462  -0.1201   0.7377   0.4852
  -1.500   0.3160   0.01233   0.00450  -0.1203   0.7279   0.4885
  -1.250   0.3436   0.01233   0.00445  -0.1202   0.7174   0.4912
  -1.000   0.3712   0.01234   0.00444  -0.1201   0.7074   0.4940
  -0.750   0.3993   0.01237   0.00441  -0.1201   0.6977   0.4971
  -0.500   0.4266   0.01239   0.00439  -0.1200   0.6872   0.5004
  -0.250   0.4545   0.01242   0.00435  -0.1200   0.6775   0.5037
   0.000   0.4821   0.01246   0.00433  -0.1199   0.6677   0.5067
   0.250   0.5091   0.01249   0.00437  -0.1197   0.6577   0.5096
   0.500   0.5364   0.01255   0.00441  -0.1196   0.6483   0.5129
   0.750   0.5635   0.01261   0.00444  -0.1194   0.6383   0.5166
   1.000   0.5908   0.01268   0.00447  -0.1193   0.6285   0.5204
   1.250   0.6179   0.01275   0.00451  -0.1192   0.6192   0.5234
   1.500   0.6444   0.01281   0.00460  -0.1189   0.6090   0.5265
   1.750   0.6711   0.01290   0.00468  -0.1187   0.5996   0.5301
   2.000   0.6978   0.01300   0.00477  -0.1184   0.5897   0.5344
   2.250   0.7245   0.01310   0.00486  -0.1182   0.5797   0.5386
   2.500   0.7507   0.01320   0.00497  -0.1179   0.5703   0.5420
   2.750   0.7767   0.01330   0.00511  -0.1175   0.5599   0.5457
   3.000   0.8029   0.01343   0.00524  -0.1172   0.5499   0.5500
   3.250   0.8288   0.01358   0.00536  -0.1169   0.5398   0.5547
   3.500   0.8542   0.01369   0.00554  -0.1164   0.5287   0.5586
   3.750   0.8795   0.01383   0.00572  -0.1159   0.5178   0.5634
   4.000   0.9047   0.01401   0.00587  -0.1154   0.5071   0.5686
   4.250   0.9294   0.01416   0.00607  -0.1148   0.4952   0.5731
   4.500   0.9540   0.01433   0.00629  -0.1143   0.4838   0.5777
   4.750   0.9785   0.01452   0.00650  -0.1136   0.4726   0.5835
   5.000   1.0023   0.01473   0.00673  -0.1129   0.4612   0.5891
   5.250   1.0261   0.01492   0.00698  -0.1122   0.4489   0.5949
   5.500   1.0495   0.01515   0.00723  -0.1114   0.4364   0.6016
   5.750   1.0722   0.01538   0.00752  -0.1105   0.4238   0.6073
   6.000   1.0945   0.01564   0.00781  -0.1095   0.4110   0.6141
   6.250   1.1162   0.01592   0.00812  -0.1085   0.3978   0.6213
   6.500   1.1374   0.01620   0.00845  -0.1074   0.3841   0.6290
   6.750   1.1583   0.01651   0.00881  -0.1062   0.3698   0.6373
   7.000   1.1783   0.01684   0.00918  -0.1049   0.3553   0.6460
   7.250   1.1974   0.01720   0.00958  -0.1034   0.3401   0.6549
   7.500   1.2155   0.01759   0.01000  -0.1018   0.3243   0.6650
   7.750   1.2314   0.01801   0.01046  -0.0998   0.3078   0.6756
   8.000   1.2460   0.01846   0.01094  -0.0976   0.2915   0.6874
   8.250   1.2602   0.01896   0.01147  -0.0954   0.2742   0.7006
   8.500   1.2737   0.01952   0.01206  -0.0931   0.2561   0.7151
   8.750   1.2857   0.02015   0.01271  -0.0907   0.2381   0.7310
   9.000   1.2964   0.02084   0.01343  -0.0882   0.2208   0.7492
   9.250   1.3058   0.02159   0.01420  -0.0855   0.2041   0.7717
   9.500   1.3140   0.02236   0.01503  -0.0827   0.1891   0.8011
   9.750   1.3197   0.02308   0.01585  -0.0794   0.1756   0.8484
  10.000   1.3220   0.02374   0.01661  -0.0757   0.1636   1.0000
  10.250   1.3309   0.02484   0.01768  -0.0737   0.1504   1.0000
  10.500   1.3393   0.02601   0.01885  -0.0718   0.1386   1.0000
  10.750   1.3465   0.02730   0.02012  -0.0699   0.1277   1.0000
  11.000   1.3538   0.02865   0.02147  -0.0681   0.1175   1.0000
  11.250   1.3614   0.03002   0.02287  -0.0665   0.1086   1.0000
  11.500   1.3669   0.03161   0.02446  -0.0649   0.1005   1.0000
  11.750   1.3726   0.03325   0.02613  -0.0634   0.0925   1.0000
  12.000   1.3780   0.03497   0.02790  -0.0621   0.0857   1.0000
  12.250   1.3816   0.03692   0.02988  -0.0609   0.0792   1.0000
  12.500   1.3862   0.03885   0.03188  -0.0598   0.0734   1.0000
  12.750   1.3885   0.04107   0.03413  -0.0588   0.0679   1.0000
  13.000   1.3917   0.04329   0.03642  -0.0581   0.0632   1.0000
  13.250   1.3938   0.04570   0.03889  -0.0574   0.0586   1.0000
  13.500   1.3937   0.04841   0.04166  -0.0569   0.0549   1.0000
  13.750   1.3963   0.05094   0.04429  -0.0566   0.0512   1.0000
  14.000   1.3957   0.05393   0.04734  -0.0564   0.0480   1.0000
  14.250   1.3942   0.05710   0.05059  -0.0564   0.0453   1.0000
  14.500   1.3952   0.06009   0.05370  -0.0565   0.0426   1.0000
  14.750   1.3937   0.06350   0.05721  -0.0569   0.0401   1.0000
  15.000   1.3893   0.06738   0.06116  -0.0575   0.0382   1.0000
  15.250   1.3881   0.07094   0.06484  -0.0581   0.0363   1.0000
  15.500   1.3865   0.07465   0.06868  -0.0589   0.0344   1.0000
  15.750   1.3830   0.07875   0.07288  -0.0599   0.0327   1.0000
  16.000   1.3770   0.08331   0.07751  -0.0613   0.0313   1.0000
  16.250   1.3724   0.08776   0.08208  -0.0627   0.0300   1.0000
  16.500   1.3696   0.09202   0.08648  -0.0641   0.0287   1.0000
  16.750   1.3656   0.09654   0.09113  -0.0657   0.0274   1.0000
  17.000   1.3603   0.10139   0.09608  -0.0676   0.0263   1.0000
  17.250   1.3533   0.10657   0.10135  -0.0698   0.0254   1.0000
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