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EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 542 AIRFOIL (e542-il)
Reynolds number: 200,000
Max Cl/Cd: 52.5 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e542-il-200000.txt
Download as CSV file: xf-e542-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 542 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  -0.4542   0.08802   0.08463  -0.0676   1.0000   0.0500
 -11.000  -0.4625   0.08403   0.08067  -0.0679   1.0000   0.0492
 -10.750  -0.4956   0.07886   0.07544  -0.0687   1.0000   0.0496
 -10.500  -0.5130   0.07564   0.07224  -0.0673   1.0000   0.0491
 -10.250  -0.5560   0.07341   0.06998  -0.0628   1.0000   0.0497
  -8.250  -0.5486   0.03590   0.02935  -0.0601   0.9324   0.0303
  -8.000  -0.5122   0.03079   0.02357  -0.0613   0.9287   0.0255
  -7.750  -0.4658   0.02755   0.02005  -0.0647   0.9258   0.0246
  -7.500  -0.4133   0.02489   0.01712  -0.0687   0.9218   0.0243
  -7.250  -0.3553   0.02294   0.01499  -0.0733   0.9192   0.0252
  -7.000  -0.3077   0.02144   0.01346  -0.0765   0.9142   0.0267
  -6.750  -0.2752   0.02041   0.01243  -0.0777   0.9047   0.0297
  -6.500  -0.2482   0.01951   0.01151  -0.0781   0.8950   0.0356
  -6.250  -0.2334   0.01869   0.01069  -0.0763   0.8826   0.0439
  -6.000  -0.2224   0.01774   0.00985  -0.0738   0.8717   0.0640
  -5.750  -0.2224   0.01636   0.00899  -0.0697   0.8612   0.1486
  -5.500  -0.2341   0.01519   0.00842  -0.0636   0.8488   0.2635
  -5.250  -0.2567   0.01420   0.00795  -0.0552   0.8376   0.3739
  -5.000  -0.2158   0.01682   0.01203  -0.0522   0.8327   0.7028
  -4.750  -0.2139   0.01754   0.01262  -0.0467   0.8248   0.7283
  -4.500  -0.1449   0.02035   0.01520  -0.0507   0.8201   0.7472
  -4.250  -0.1009   0.02168   0.01632  -0.0520   0.8146   0.7609
  -4.000  -0.0090   0.02336   0.01773  -0.0613   0.8119   0.7657
  -3.750   0.0374   0.02438   0.01862  -0.0632   0.8059   0.7794
  -3.500   0.0839   0.02520   0.01931  -0.0654   0.8004   0.7943
  -3.250   0.1338   0.02524   0.01918  -0.0691   0.7958   0.7994
  -3.000   0.1489   0.02533   0.01922  -0.0670   0.7890   0.8103
  -2.750   0.1922   0.02515   0.01891  -0.0698   0.7834   0.8147
  -2.500   0.2084   0.02525   0.01892  -0.0679   0.7785   0.8257
  -2.250   0.2509   0.02495   0.01856  -0.0708   0.7732   0.8299
  -2.000   0.2657   0.02511   0.01867  -0.0686   0.7673   0.8413
  -1.750   0.3144   0.02467   0.01813  -0.0726   0.7631   0.8464
  -1.500   0.3839   0.02492   0.01831  -0.0790   0.7593   0.8835
  -1.250   0.4063   0.02532   0.01871  -0.0781   0.7538   0.9012
  -1.000   0.4525   0.02403   0.01737  -0.0823   0.7492   0.9051
  -0.750   0.4730   0.02433   0.01760  -0.0813   0.7452   0.9164
  -0.500   0.5112   0.02335   0.01664  -0.0841   0.7401   0.9203
  -0.250   0.5301   0.02361   0.01689  -0.0829   0.7350   0.9310
   0.000   0.5683   0.02268   0.01593  -0.0857   0.7309   0.9344
   0.500   0.6241   0.02209   0.01536  -0.0872   0.7214   0.9480
   0.750   0.6478   0.02231   0.01559  -0.0870   0.7168   0.9576
   1.250   0.7135   0.02110   0.01441  -0.0905   0.7076   0.9673
   1.500   0.7408   0.02078   0.01412  -0.0911   0.7024   0.9731
   1.750   0.7748   0.02028   0.01362  -0.0931   0.6978   0.9787
   2.000   0.8043   0.01993   0.01331  -0.0941   0.6922   0.9847
   2.250   0.8363   0.01940   0.01285  -0.0958   0.6859   0.9897
   2.750   0.9017   0.01840   0.01191  -0.0992   0.6744   0.9988
   3.000   0.9258   0.01820   0.01177  -0.0991   0.6681   1.0000
   3.750   0.8236   0.02159   0.01519  -0.0639   0.6536   0.9319
   4.000   0.8807   0.02097   0.01457  -0.0698   0.6475   0.9467
   4.250   0.9237   0.02051   0.01426  -0.0732   0.6389   0.9604
   4.500   0.8199   0.02159   0.01527  -0.0487   0.6363   0.9155
   4.750   0.8427   0.02132   0.01498  -0.0480   0.6310   0.9156
   5.000   0.8553   0.02117   0.01497  -0.0456   0.6229   0.9144
   5.250   0.8765   0.02088   0.01468  -0.0446   0.6164   0.9139
   5.500   0.8825   0.02080   0.01469  -0.0408   0.6088   0.9140
   5.750   0.8957   0.02058   0.01450  -0.0383   0.6016   0.9137
   6.000   0.9039   0.02041   0.01440  -0.0348   0.5940   0.9131
   6.250   0.9077   0.02021   0.01425  -0.0305   0.5863   0.9129
   6.500   0.9045   0.02003   0.01410  -0.0246   0.5793   0.9137
   6.750   0.8856   0.01979   0.01391  -0.0159   0.5720   0.9139
   7.000   0.8885   0.01946   0.01358  -0.0113   0.5643   0.9144
   7.250   0.8788   0.01916   0.01336  -0.0045   0.5555   0.9160
   7.500   0.8909   0.01886   0.01312  -0.0017   0.5448   0.9168
   7.750   0.9065   0.01854   0.01282   0.0004   0.5337   0.9175
   8.000   0.9104   0.01827   0.01264   0.0046   0.5209   0.9186
   8.250   0.9149   0.01804   0.01249   0.0087   0.5071   0.9198
   8.500   0.9186   0.01782   0.01232   0.0129   0.4919   0.9212
   8.750   0.9209   0.01765   0.01218   0.0173   0.4754   0.9234
   9.000   0.9256   0.01763   0.01215   0.0210   0.4563   0.9253
   9.250   0.9292   0.01780   0.01233   0.0246   0.4331   0.9270
   9.500   0.9335   0.01814   0.01259   0.0278   0.4068   0.9287
   9.750   0.9368   0.01869   0.01305   0.0308   0.3792   0.9303
  10.000   0.9367   0.01936   0.01364   0.0343   0.3512   0.9321
  10.250   0.9363   0.02022   0.01441   0.0374   0.3244   0.9342
  10.500   0.9345   0.02127   0.01536   0.0404   0.2985   0.9367
  10.750   0.9342   0.02242   0.01645   0.0429   0.2733   0.9396
  11.000   0.9342   0.02375   0.01770   0.0450   0.2488   0.9421
  11.250   0.9346   0.02520   0.01908   0.0467   0.2256   0.9443
  11.500   0.9351   0.02669   0.02051   0.0484   0.2041   0.9467
  11.750   0.9366   0.02827   0.02206   0.0497   0.1833   0.9494
  12.000   0.9374   0.03003   0.02375   0.0508   0.1644   0.9523
  12.250   0.9395   0.03183   0.02551   0.0516   0.1466   0.9553
  12.500   0.9427   0.03369   0.02735   0.0521   0.1297   0.9584
  12.750   0.9467   0.03570   0.02935   0.0522   0.1143   0.9615
  13.000   0.9506   0.03786   0.03150   0.0521   0.1002   0.9651
  13.250   0.9549   0.04018   0.03381   0.0517   0.0877   0.9693
  13.500   0.9605   0.04263   0.03625   0.0508   0.0770   0.9738
  13.750   0.9658   0.04516   0.03878   0.0498   0.0683   0.9794
  14.000   0.9692   0.04762   0.04122   0.0491   0.0614   0.9917
  14.250   0.9749   0.04984   0.04353   0.0488   0.0553   1.0000
  14.500   0.9781   0.05228   0.04597   0.0485   0.0506   1.0000
  14.750   0.9840   0.05463   0.04840   0.0478   0.0461   1.0000
  15.000   0.9881   0.05712   0.05091   0.0473   0.0423   1.0000
  15.250   0.9933   0.05965   0.05350   0.0465   0.0388   1.0000
  15.500   0.9977   0.06222   0.05611   0.0460   0.0356   1.0000
  15.750   1.0024   0.06494   0.05892   0.0450   0.0328   1.0000
  16.000   1.0050   0.06784   0.06187   0.0441   0.0299   1.0000
  16.250   1.0087   0.07077   0.06491   0.0430   0.0276   1.0000
  16.500   1.0129   0.07352   0.06767   0.0423   0.0254   1.0000
  16.750   1.0144   0.07689   0.07121   0.0410   0.0234   1.0000
  17.000   1.0155   0.08017   0.07446   0.0396   0.0213   1.0000
  17.250   1.0148   0.08399   0.07850   0.0381   0.0199   1.0000
  17.500   1.0154   0.08756   0.08211   0.0363   0.0186   1.0000
  17.750   1.0137   0.09149   0.08617   0.0348   0.0172   1.0000
  18.000   1.0124   0.09555   0.09042   0.0331   0.0164   1.0000
  18.250   1.0111   0.09962   0.09463   0.0311   0.0158   1.0000
  18.500   1.0131   0.10305   0.09806   0.0294   0.0150   1.0000
  18.750   1.0034   0.10866   0.10389   0.0264   0.0142   1.0000
  19.000   0.9929   0.11466   0.11013   0.0231   0.0138   1.0000
  19.250   0.9847   0.12035   0.11601   0.0198   0.0135   1.0000
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