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EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 546 AIRFOIL (e546-il)
Reynolds number: 200,000
Max Cl/Cd: 61.24 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e546-il-200000.txt
Download as CSV file: xf-e546-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 546 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3615   0.09009   0.08691  -0.0561   1.0000   0.0618
 -11.000  -0.3962   0.08044   0.07726  -0.0620   1.0000   0.0622
 -10.750  -0.4264   0.07392   0.07070  -0.0643   1.0000   0.0622
 -10.500  -0.5476   0.07365   0.07009  -0.0644   1.0000   0.0556
 -10.250  -0.5656   0.07047   0.06688  -0.0633   1.0000   0.0559
 -10.000  -0.5857   0.06774   0.06412  -0.0612   1.0000   0.0563
  -9.750  -0.6091   0.06563   0.06199  -0.0576   1.0000   0.0566
  -9.500  -0.6414   0.06452   0.06089  -0.0515   1.0000   0.0565
  -9.250  -0.6782   0.06417   0.06054  -0.0437   1.0000   0.0562
  -9.000  -0.6806   0.06157   0.05786  -0.0429   0.9963   0.0576
  -8.000  -0.6300   0.03414   0.02746  -0.0439   0.9622   0.0256
  -7.750  -0.5937   0.03073   0.02377  -0.0460   0.9590   0.0244
  -7.500  -0.5571   0.02790   0.02059  -0.0473   0.9546   0.0237
  -7.250  -0.5181   0.02579   0.01824  -0.0490   0.9500   0.0237
  -7.000  -0.4748   0.02400   0.01634  -0.0515   0.9472   0.0246
  -6.750  -0.4305   0.02253   0.01473  -0.0543   0.9448   0.0262
  -6.500  -0.3946   0.02104   0.01337  -0.0564   0.9394   0.0290
  -6.250  -0.3616   0.01980   0.01216  -0.0582   0.9317   0.0350
  -6.000  -0.3336   0.01848   0.01085  -0.0592   0.9227   0.0418
  -5.750  -0.3102   0.01701   0.00949  -0.0595   0.9127   0.0661
  -5.250  -0.3131   0.01324   0.00733  -0.0525   0.8828   0.3571
  -5.000  -0.3075   0.01308   0.00839  -0.0474   0.8708   0.6219
  -4.750  -0.2752   0.01419   0.00934  -0.0467   0.8630   0.6660
  -4.500  -0.2459   0.01562   0.01069  -0.0448   0.8526   0.6866
  -4.250  -0.2088   0.01708   0.01204  -0.0440   0.8456   0.7012
  -4.000  -0.1814   0.01786   0.01271  -0.0426   0.8352   0.7126
  -3.750  -0.1448   0.01898   0.01370  -0.0421   0.8274   0.7216
  -3.500  -0.1030   0.02039   0.01503  -0.0416   0.8190   0.7311
  -3.250  -0.0544   0.02185   0.01634  -0.0423   0.8123   0.7449
  -3.000  -0.0127   0.02235   0.01673  -0.0433   0.8030   0.7503
  -2.750  -0.0068   0.02188   0.01615  -0.0404   0.7931   0.7594
  -2.500   0.0283   0.02190   0.01605  -0.0412   0.7846   0.7617
  -2.250   0.0566   0.02182   0.01587  -0.0412   0.7760   0.7650
  -2.000   0.0527   0.02112   0.01506  -0.0372   0.7667   0.7740
  -1.750   0.0826   0.02104   0.01491  -0.0373   0.7580   0.7757
  -1.500   0.1131   0.02092   0.01468  -0.0377   0.7506   0.7777
  -1.250   0.1365   0.02076   0.01447  -0.0370   0.7421   0.7805
  -1.000   0.1561   0.02046   0.01407  -0.0361   0.7345   0.7841
  -0.750   0.1592   0.01983   0.01338  -0.0335   0.7260   0.7898
  -0.500   0.1870   0.01966   0.01314  -0.0334   0.7190   0.7912
  -0.250   0.2118   0.01952   0.01295  -0.0330   0.7116   0.7928
   0.000   0.2364   0.01933   0.01271  -0.0327   0.7042   0.7945
   0.250   0.2603   0.01917   0.01249  -0.0324   0.6976   0.7967
   0.500   0.2808   0.01891   0.01221  -0.0317   0.6900   0.7987
   0.750   0.3056   0.01868   0.01188  -0.0319   0.6843   0.8010
   1.000   0.3238   0.01839   0.01159  -0.0312   0.6763   0.8036
   1.250   0.3491   0.01811   0.01123  -0.0318   0.6703   0.8055
   1.500   0.3731   0.01801   0.01115  -0.0312   0.6635   0.8067
   1.750   0.3982   0.01790   0.01103  -0.0310   0.6568   0.8080
   2.000   0.4260   0.01781   0.01087  -0.0314   0.6514   0.8091
   2.250   0.4484   0.01771   0.01083  -0.0308   0.6439   0.8104
   2.500   0.4759   0.01761   0.01069  -0.0312   0.6381   0.8118
   2.750   0.5003   0.01757   0.01068  -0.0311   0.6317   0.8138
   3.000   0.5261   0.01748   0.01059  -0.0312   0.6249   0.8155
   3.250   0.5553   0.01742   0.01048  -0.0321   0.6194   0.8169
   3.500   0.5790   0.01735   0.01048  -0.0320   0.6116   0.8185
   3.750   0.6088   0.01727   0.01035  -0.0330   0.6055   0.8199
   4.000   0.6334   0.01724   0.01039  -0.0329   0.5980   0.8215
   4.250   0.6594   0.01717   0.01033  -0.0328   0.5911   0.8230
   4.500   0.6844   0.01718   0.01038  -0.0325   0.5842   0.8244
   4.750   0.7098   0.01715   0.01040  -0.0324   0.5766   0.8258
   5.000   0.7369   0.01715   0.01042  -0.0326   0.5698   0.8272
   5.250   0.7613   0.01713   0.01047  -0.0323   0.5614   0.8289
   5.500   0.7887   0.01712   0.01048  -0.0326   0.5539   0.8305
   5.750   0.8135   0.01709   0.01052  -0.0324   0.5448   0.8323
   6.000   0.8398   0.01710   0.01056  -0.0326   0.5363   0.8343
   6.250   0.8668   0.01708   0.01058  -0.0329   0.5271   0.8366
   6.500   0.8887   0.01707   0.01067  -0.0319   0.5176   0.8383
   6.750   0.9147   0.01705   0.01065  -0.0318   0.5085   0.8399
   7.000   0.9347   0.01703   0.01077  -0.0306   0.4971   0.8419
   7.250   0.9566   0.01704   0.01086  -0.0297   0.4856   0.8440
   7.500   0.9790   0.01704   0.01091  -0.0290   0.4735   0.8462
   7.750   1.0008   0.01706   0.01098  -0.0282   0.4603   0.8486
   8.000   1.0211   0.01711   0.01107  -0.0272   0.4454   0.8511
   8.250   1.0381   0.01716   0.01121  -0.0255   0.4292   0.8536
   8.500   1.0521   0.01724   0.01139  -0.0232   0.4112   0.8565
   8.750   1.0649   0.01739   0.01160  -0.0208   0.3908   0.8597
   9.000   1.0756   0.01765   0.01183  -0.0181   0.3686   0.8631
   9.250   1.0826   0.01798   0.01215  -0.0150   0.3429   0.8667
   9.500   1.0857   0.01847   0.01260  -0.0112   0.3166   0.8703
   9.750   1.0866   0.01918   0.01323  -0.0073   0.2897   0.8745
  10.000   1.0869   0.02008   0.01404  -0.0038   0.2629   0.8794
  10.250   1.0872   0.02110   0.01500  -0.0006   0.2373   0.8844
  10.500   1.0842   0.02225   0.01608   0.0029   0.2156   0.8903
  10.750   1.0842   0.02351   0.01731   0.0055   0.1934   0.8974
  11.000   1.0818   0.02490   0.01867   0.0083   0.1745   0.9049
  11.250   1.0802   0.02650   0.02023   0.0105   0.1567   0.9139
  11.500   1.0792   0.02809   0.02185   0.0125   0.1398   0.9254
  12.000   1.0838   0.03210   0.02591   0.0133   0.1082   1.0000
  12.250   1.0861   0.03450   0.02826   0.0132   0.0954   1.0000
  12.500   1.0875   0.03700   0.03073   0.0131   0.0846   1.0000
  12.750   1.0869   0.03968   0.03337   0.0132   0.0759   1.0000
  13.000   1.0877   0.04228   0.03595   0.0131   0.0683   1.0000
  13.250   1.0899   0.04478   0.03850   0.0131   0.0617   1.0000
  13.500   1.0879   0.04768   0.04132   0.0131   0.0565   1.0000
  13.750   1.0923   0.05010   0.04386   0.0129   0.0514   1.0000
  14.000   1.0913   0.05296   0.04665   0.0129   0.0475   1.0000
  14.250   1.0954   0.05551   0.04934   0.0125   0.0435   1.0000
  14.500   1.0953   0.05837   0.05212   0.0123   0.0401   1.0000
  14.750   1.0985   0.06114   0.05505   0.0118   0.0370   1.0000
  15.000   1.0992   0.06412   0.05803   0.0112   0.0342   1.0000
  15.250   1.1015   0.06700   0.06100   0.0109   0.0317   1.0000
  15.500   1.1007   0.07037   0.06443   0.0098   0.0289   1.0000
  15.750   1.1032   0.07321   0.06729   0.0095   0.0269   1.0000
  16.000   1.1020   0.07685   0.07109   0.0083   0.0247   1.0000
  16.250   1.1050   0.07969   0.07387   0.0077   0.0230   1.0000
  16.500   1.1014   0.08384   0.07824   0.0063   0.0212   1.0000
  16.750   1.1005   0.08755   0.08203   0.0048   0.0198   1.0000
  17.000   1.1046   0.09029   0.08471   0.0043   0.0186   1.0000
  17.250   1.0999   0.09487   0.08956   0.0026   0.0176   1.0000
  17.500   1.0970   0.09912   0.09397   0.0009   0.0167   1.0000
  17.750   1.0958   0.10305   0.09798  -0.0008   0.0160   1.0000
  18.000   1.1023   0.10551   0.10038  -0.0011   0.0152   1.0000
  18.250   1.0920   0.11129   0.10643  -0.0041   0.0149   1.0000
  18.500   1.0800   0.11757   0.11297  -0.0074   0.0146   1.0000
  18.750   1.0701   0.12353   0.11914  -0.0107   0.0144   1.0000
  19.000   1.0574   0.13022   0.12605  -0.0145   0.0142   1.0000
  19.250   1.0449   0.13707   0.13310  -0.0187   0.0139   1.0000
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