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EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 266 AIRFOIL (e266-il)
Reynolds number: 200,000
Max Cl/Cd: 59.64 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e266-il-200000-n5.txt
Download as CSV file: xf-e266-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 266 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3375   0.07130   0.06655  -0.1033   0.7493   0.0149
 -12.000  -0.3512   0.06596   0.06112  -0.1067   0.7429   0.0148
 -11.750  -0.3768   0.06012   0.05509  -0.1093   0.7377   0.0147
 -11.500  -0.3962   0.05598   0.05078  -0.1100   0.7326   0.0146
 -11.250  -0.4175   0.05212   0.04672  -0.1094   0.7275   0.0145
 -11.000  -0.4370   0.04876   0.04312  -0.1078   0.7228   0.0145
 -10.500  -0.4631   0.04349   0.03740  -0.1028   0.7143   0.0144
 -10.250  -0.4742   0.04101   0.03466  -0.0996   0.7101   0.0144
 -10.000  -0.4831   0.03877   0.03212  -0.0960   0.7061   0.0145
  -9.750  -0.4905   0.03676   0.02975  -0.0919   0.7028   0.0146
  -9.500  -0.4881   0.03495   0.02767  -0.0890   0.6994   0.0146
  -9.250  -0.4840   0.03314   0.02545  -0.0862   0.6961   0.0149
  -9.000  -0.4735   0.03142   0.02353  -0.0844   0.6930   0.0154
  -8.750  -0.4584   0.03025   0.02222  -0.0832   0.6902   0.0158
  -8.500  -0.4413   0.02888   0.02061  -0.0820   0.6877   0.0160
  -8.000  -0.3998   0.02623   0.01754  -0.0805   0.6830   0.0164
  -7.750  -0.3765   0.02508   0.01623  -0.0801   0.6805   0.0166
  -7.500  -0.3524   0.02402   0.01504  -0.0798   0.6780   0.0169
  -7.250  -0.3282   0.02309   0.01400  -0.0795   0.6756   0.0172
  -7.000  -0.3045   0.02220   0.01299  -0.0790   0.6733   0.0176
  -6.750  -0.2820   0.02146   0.01214  -0.0784   0.6712   0.0181
  -6.500  -0.2606   0.02080   0.01137  -0.0775   0.6693   0.0185
  -6.250  -0.2408   0.02016   0.01070  -0.0765   0.6672   0.0190
  -6.000  -0.2222   0.01956   0.01011  -0.0753   0.6651   0.0198
  -5.750  -0.2023   0.01912   0.00964  -0.0743   0.6631   0.0212
  -5.500  -0.1824   0.01869   0.00915  -0.0732   0.6611   0.0224
  -5.250  -0.1626   0.01827   0.00866  -0.0721   0.6592   0.0234
  -5.000  -0.1427   0.01784   0.00819  -0.0710   0.6575   0.0248
  -4.750  -0.1215   0.01751   0.00778  -0.0700   0.6558   0.0267
  -4.500  -0.1004   0.01716   0.00739  -0.0690   0.6542   0.0301
  -4.250  -0.0795   0.01681   0.00704  -0.0681   0.6526   0.0388
  -4.000  -0.0622   0.01626   0.00673  -0.0666   0.6506   0.0782
  -3.750  -0.0464   0.01565   0.00646  -0.0650   0.6488   0.1511
  -3.500  -0.0344   0.01484   0.00618  -0.0629   0.6471   0.2680
  -3.250  -0.0282   0.01379   0.00588  -0.0597   0.6454   0.4339
  -3.000  -0.0186   0.01335   0.00656  -0.0553   0.6438   0.6553
  -2.750   0.0065   0.01406   0.00735  -0.0537   0.6422   0.7338
  -2.500   0.0313   0.01459   0.00779  -0.0525   0.6406   0.7599
  -2.250   0.0573   0.01504   0.00814  -0.0517   0.6390   0.7745
  -2.000   0.0831   0.01554   0.00854  -0.0507   0.6376   0.7884
  -1.750   0.1131   0.01610   0.00903  -0.0503   0.6364   0.7954
  -1.500   0.1352   0.01620   0.00907  -0.0494   0.6348   0.8043
  -1.250   0.1625   0.01642   0.00926  -0.0491   0.6331   0.8073
  -1.000   0.1885   0.01655   0.00935  -0.0488   0.6313   0.8108
  -0.750   0.2131   0.01658   0.00932  -0.0484   0.6293   0.8151
  -0.500   0.2363   0.01652   0.00919  -0.0481   0.6275   0.8201
  -0.250   0.2631   0.01659   0.00922  -0.0480   0.6260   0.8219
   0.000   0.2898   0.01665   0.00923  -0.0480   0.6246   0.8239
   0.250   0.3165   0.01669   0.00922  -0.0480   0.6232   0.8262
   0.500   0.3432   0.01671   0.00918  -0.0481   0.6218   0.8287
   0.750   0.3699   0.01673   0.00912  -0.0482   0.6205   0.8314
   1.000   0.3927   0.01674   0.00914  -0.0479   0.6186   0.8348
   1.250   0.4167   0.01680   0.00922  -0.0476   0.6167   0.8366
   1.500   0.4413   0.01687   0.00932  -0.0472   0.6146   0.8381
   1.750   0.4662   0.01694   0.00940  -0.0470   0.6126   0.8398
   2.000   0.4917   0.01700   0.00946  -0.0469   0.6108   0.8414
   2.250   0.5175   0.01705   0.00951  -0.0469   0.6091   0.8432
   2.500   0.5440   0.01709   0.00954  -0.0470   0.6075   0.8453
   2.750   0.5714   0.01712   0.00954  -0.0474   0.6060   0.8472
   3.000   0.5995   0.01716   0.00957  -0.0479   0.6046   0.8489
   3.250   0.6222   0.01728   0.00975  -0.0475   0.6023   0.8510
   3.500   0.6437   0.01742   0.00997  -0.0467   0.5996   0.8524
   3.750   0.6670   0.01754   0.01016  -0.0462   0.5970   0.8539
   4.000   0.6918   0.01761   0.01027  -0.0460   0.5946   0.8552
   4.250   0.7179   0.01765   0.01033  -0.0461   0.5924   0.8565
   4.500   0.7459   0.01765   0.01036  -0.0464   0.5903   0.8579
   4.750   0.7755   0.01765   0.01034  -0.0471   0.5885   0.8592
   5.000   0.7920   0.01786   0.01070  -0.0455   0.5843   0.8616
   5.250   0.8139   0.01796   0.01087  -0.0449   0.5805   0.8638
   5.500   0.8396   0.01796   0.01092  -0.0449   0.5773   0.8654
   5.750   0.8680   0.01788   0.01087  -0.0453   0.5746   0.8665
   6.000   0.8932   0.01787   0.01092  -0.0450   0.5713   0.8677
   6.250   0.9081   0.01804   0.01125  -0.0431   0.5661   0.8693
   6.500   0.9311   0.01802   0.01130  -0.0424   0.5619   0.8708
   6.750   0.9597   0.01786   0.01117  -0.0427   0.5584   0.8722
   7.000   0.9745   0.01799   0.01144  -0.0408   0.5527   0.8746
   7.250   0.9935   0.01796   0.01151  -0.0394   0.5467   0.8769
   7.500   1.0220   0.01773   0.01130  -0.0397   0.5421   0.8784
   7.750   1.0292   0.01798   0.01172  -0.0365   0.5341   0.8809
   8.000   1.0514   0.01780   0.01161  -0.0356   0.5280   0.8824
   8.250   1.0544   0.01800   0.01196  -0.0314   0.5194   0.8848
   8.500   1.0693   0.01793   0.01195  -0.0293   0.5112   0.8870
   8.750   1.0753   0.01816   0.01227  -0.0258   0.5002   0.8902
   9.000   1.0820   0.01848   0.01269  -0.0226   0.4883   0.8935
   9.250   1.0915   0.01876   0.01302  -0.0201   0.4739   0.8964
   9.500   1.1006   0.01902   0.01326  -0.0174   0.4559   0.8989
   9.750   1.1045   0.01955   0.01373  -0.0142   0.4312   0.9020
  10.000   1.1025   0.02050   0.01451  -0.0107   0.3995   0.9057
  10.250   1.0953   0.02198   0.01581  -0.0070   0.3681   0.9098
  10.500   1.0842   0.02394   0.01760  -0.0036   0.3361   0.9139
  10.750   1.0794   0.02581   0.01938  -0.0012   0.3116   0.9184
  11.000   1.0694   0.02816   0.02157   0.0012   0.2815   0.9233
  11.250   1.0644   0.03041   0.02371   0.0029   0.2563   0.9273
  11.500   1.0574   0.03297   0.02613   0.0043   0.2264   0.9317
  11.750   1.0580   0.03508   0.02817   0.0051   0.2044   0.9362
  12.000   1.0603   0.03736   0.03039   0.0053   0.1829   0.9402
  12.250   1.0644   0.03971   0.03267   0.0050   0.1601   0.9448
  12.500   1.0683   0.04232   0.03520   0.0043   0.1357   0.9499
  12.750   1.0744   0.04496   0.03775   0.0032   0.1133   0.9558
  13.000   1.0799   0.04716   0.03992   0.0025   0.0953   0.9870
  13.250   1.0785   0.04925   0.04193   0.0041   0.0819   1.0000
  13.500   1.0813   0.05155   0.04417   0.0044   0.0677   1.0000
  13.750   1.0840   0.05392   0.04649   0.0046   0.0553   1.0000
  14.000   1.0876   0.05626   0.04881   0.0047   0.0446   1.0000
  14.250   1.0896   0.05880   0.05132   0.0048   0.0343   1.0000
  14.500   1.0920   0.06135   0.05387   0.0048   0.0276   1.0000
  14.750   1.0937   0.06405   0.05658   0.0048   0.0226   1.0000
  15.000   1.0969   0.06665   0.05922   0.0047   0.0206   1.0000
  15.250   1.0990   0.06941   0.06205   0.0045   0.0181   1.0000
  15.500   1.1027   0.07203   0.06475   0.0042   0.0173   1.0000
  15.750   1.1035   0.07506   0.06785   0.0038   0.0162   1.0000
  16.000   1.1062   0.07792   0.07082   0.0034   0.0156   1.0000
  16.250   1.1080   0.08092   0.07393   0.0028   0.0146   1.0000
  16.500   1.1089   0.08409   0.07720   0.0022   0.0142   1.0000
  16.750   1.1084   0.08748   0.08069   0.0015   0.0137   1.0000
  17.000   1.1066   0.09112   0.08442   0.0006   0.0135   1.0000
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