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EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 546 AIRFOIL (e546-il)
Reynolds number: 200,000
Max Cl/Cd: 61.39 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e546-il-200000-n5.txt
Download as CSV file: xf-e546-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5003   0.08964   0.08598  -0.0545   1.0000   0.0102
 -12.250  -0.5530   0.07410   0.07020  -0.0636   1.0000   0.0098
 -12.000  -0.5944   0.06541   0.06126  -0.0665   1.0000   0.0095
 -11.500  -0.6700   0.05257   0.04765  -0.0650   1.0000   0.0091
 -11.250  -0.6845   0.04958   0.04447  -0.0631   1.0000   0.0091
 -11.000  -0.6969   0.04695   0.04168  -0.0606   1.0000   0.0090
 -10.750  -0.7092   0.04454   0.03906  -0.0576   1.0000   0.0090
 -10.500  -0.7194   0.04243   0.03679  -0.0543   1.0000   0.0090
 -10.250  -0.7303   0.04061   0.03479  -0.0502   1.0000   0.0090
 -10.000  -0.7436   0.03911   0.03313  -0.0452   1.0000   0.0090
  -9.750  -0.7247   0.03606   0.02967  -0.0465   0.9928   0.0091
  -9.500  -0.7028   0.03356   0.02688  -0.0475   0.9845   0.0091
  -9.250  -0.6795   0.03149   0.02461  -0.0481   0.9747   0.0093
  -9.000  -0.6537   0.02971   0.02265  -0.0489   0.9654   0.0094
  -8.750  -0.6230   0.02805   0.02083  -0.0504   0.9584   0.0097
  -8.500  -0.5920   0.02657   0.01920  -0.0517   0.9506   0.0100
  -8.250  -0.5570   0.02515   0.01764  -0.0536   0.9446   0.0105
  -8.000  -0.5233   0.02382   0.01617  -0.0554   0.9367   0.0111
  -7.750  -0.4886   0.02259   0.01480  -0.0576   0.9286   0.0116
  -7.500  -0.4573   0.02146   0.01364  -0.0595   0.9173   0.0126
  -7.250  -0.4249   0.02049   0.01257  -0.0615   0.9056   0.0137
  -7.000  -0.3944   0.01960   0.01161  -0.0631   0.8931   0.0159
  -6.500  -0.3480   0.01807   0.00987  -0.0632   0.8646   0.0211
  -6.250  -0.3314   0.01745   0.00918  -0.0618   0.8504   0.0259
  -6.000  -0.3153   0.01686   0.00858  -0.0602   0.8373   0.0340
  -5.750  -0.3003   0.01625   0.00801  -0.0585   0.8252   0.0516
  -5.250  -0.2754   0.01488   0.00698  -0.0543   0.8021   0.1351
  -5.000  -0.2666   0.01398   0.00642  -0.0518   0.7915   0.2154
  -4.750  -0.2635   0.01267   0.00570  -0.0485   0.7815   0.3538
  -4.500  -0.2592   0.01195   0.00613  -0.0440   0.7714   0.5746
  -4.250  -0.2338   0.01223   0.00631  -0.0433   0.7631   0.6304
  -4.000  -0.2075   0.01255   0.00651  -0.0426   0.7542   0.6507
  -3.750  -0.1807   0.01293   0.00675  -0.0420   0.7462   0.6667
  -3.500  -0.1540   0.01348   0.00722  -0.0410   0.7376   0.6823
  -3.250  -0.1270   0.01418   0.00785  -0.0399   0.7300   0.6970
  -3.000  -0.1004   0.01461   0.00818  -0.0390   0.7218   0.7065
  -2.750  -0.0744   0.01453   0.00795  -0.0389   0.7144   0.7107
  -2.500  -0.0476   0.01450   0.00782  -0.0387   0.7062   0.7122
  -2.250  -0.0205   0.01446   0.00766  -0.0387   0.6992   0.7138
  -2.000   0.0060   0.01439   0.00750  -0.0386   0.6914   0.7156
  -1.750   0.0329   0.01432   0.00730  -0.0386   0.6846   0.7175
  -1.500   0.0592   0.01422   0.00712  -0.0386   0.6768   0.7196
  -1.250   0.0861   0.01411   0.00688  -0.0388   0.6700   0.7216
  -1.000   0.1128   0.01399   0.00667  -0.0390   0.6630   0.7239
  -0.750   0.1398   0.01388   0.00645  -0.0392   0.6559   0.7259
  -0.500   0.1669   0.01384   0.00635  -0.0393   0.6494   0.7268
  -0.250   0.1938   0.01381   0.00627  -0.0393   0.6424   0.7277
   0.000   0.2211   0.01380   0.00619  -0.0393   0.6366   0.7289
   0.250   0.2477   0.01379   0.00616  -0.0393   0.6296   0.7303
   0.500   0.2748   0.01378   0.00610  -0.0394   0.6232   0.7316
   0.750   0.3020   0.01377   0.00604  -0.0395   0.6172   0.7329
   1.000   0.3289   0.01375   0.00600  -0.0396   0.6105   0.7342
   1.250   0.3563   0.01375   0.00593  -0.0398   0.6049   0.7357
   1.500   0.3833   0.01374   0.00592  -0.0400   0.5985   0.7372
   1.750   0.4106   0.01374   0.00589  -0.0402   0.5924   0.7390
   2.000   0.4382   0.01376   0.00585  -0.0405   0.5869   0.7408
   2.250   0.4650   0.01377   0.00589  -0.0406   0.5803   0.7421
   2.500   0.4919   0.01381   0.00592  -0.0406   0.5746   0.7430
   2.750   0.5185   0.01386   0.00598  -0.0406   0.5687   0.7441
   3.000   0.5450   0.01391   0.00606  -0.0405   0.5623   0.7452
   3.250   0.5719   0.01398   0.00611  -0.0406   0.5567   0.7463
   3.500   0.5980   0.01403   0.00623  -0.0405   0.5497   0.7476
   3.750   0.6243   0.01409   0.00630  -0.0404   0.5431   0.7491
   4.000   0.6505   0.01417   0.00641  -0.0404   0.5360   0.7507
   4.250   0.6764   0.01424   0.00651  -0.0403   0.5284   0.7525
   4.500   0.7026   0.01433   0.00661  -0.0402   0.5215   0.7543
   4.750   0.7284   0.01441   0.00674  -0.0401   0.5135   0.7559
   5.000   0.7544   0.01450   0.00685  -0.0401   0.5062   0.7575
   5.250   0.7791   0.01459   0.00700  -0.0397   0.4975   0.7587
   5.500   0.8036   0.01470   0.00717  -0.0393   0.4890   0.7599
   5.750   0.8276   0.01481   0.00733  -0.0388   0.4795   0.7613
   6.000   0.8513   0.01493   0.00753  -0.0383   0.4696   0.7628
   6.250   0.8747   0.01507   0.00772  -0.0377   0.4597   0.7644
   6.500   0.8976   0.01521   0.00793  -0.0370   0.4486   0.7663
   6.750   0.9201   0.01537   0.00815  -0.0363   0.4366   0.7684
   7.000   0.9418   0.01555   0.00839  -0.0355   0.4233   0.7707
   7.250   0.9627   0.01576   0.00862  -0.0345   0.4081   0.7728
   7.500   0.9817   0.01599   0.00889  -0.0332   0.3907   0.7746
   7.750   0.9986   0.01627   0.00920  -0.0315   0.3713   0.7762
   8.000   1.0135   0.01662   0.00954  -0.0295   0.3492   0.7782
   8.250   1.0255   0.01704   0.00993  -0.0271   0.3248   0.7804
   8.500   1.0337   0.01752   0.01036  -0.0240   0.2999   0.7828
   8.750   1.0400   0.01816   0.01092  -0.0208   0.2752   0.7855
   9.000   1.0466   0.01891   0.01159  -0.0179   0.2504   0.7883
   9.250   1.0516   0.01974   0.01237  -0.0148   0.2275   0.7909
   9.500   1.0560   0.02063   0.01323  -0.0119   0.2060   0.7936
   9.750   1.0595   0.02164   0.01419  -0.0090   0.1861   0.7969
  10.000   1.0642   0.02269   0.01522  -0.0066   0.1673   0.8004
  10.250   1.0681   0.02386   0.01637  -0.0043   0.1494   0.8040
  10.500   1.0717   0.02510   0.01760  -0.0022   0.1339   0.8071
  10.750   1.0752   0.02640   0.01891  -0.0002   0.1201   0.8104
  11.000   1.0792   0.02777   0.02030   0.0016   0.1080   0.8142
  11.250   1.0833   0.02925   0.02181   0.0031   0.0968   0.8184
  11.500   1.0868   0.03083   0.02342   0.0045   0.0865   0.8225
  11.750   1.0894   0.03255   0.02517   0.0057   0.0777   0.8267
  12.000   1.0935   0.03425   0.02693   0.0068   0.0694   0.8317
  12.250   1.0972   0.03607   0.02881   0.0076   0.0623   0.8372
  12.500   1.0985   0.03808   0.03088   0.0085   0.0563   0.8431
  12.750   1.1020   0.04002   0.03291   0.0092   0.0506   0.8501
  13.000   1.1035   0.04215   0.03513   0.0098   0.0459   0.8582
  13.500   1.1062   0.04664   0.03984   0.0108   0.0381   0.8810
  13.750   1.1074   0.04899   0.04233   0.0111   0.0348   0.9014
  14.750   1.1122   0.05994   0.05367   0.0093   0.0249   1.0000
  15.000   1.1111   0.06320   0.05698   0.0085   0.0231   1.0000
  15.250   1.1115   0.06637   0.06025   0.0077   0.0215   1.0000
  15.500   1.1119   0.06961   0.06358   0.0068   0.0195   1.0000
  15.750   1.1085   0.07342   0.06748   0.0056   0.0186   1.0000
  16.000   1.1083   0.07690   0.07109   0.0045   0.0170   1.0000
  16.250   1.1059   0.08076   0.07506   0.0031   0.0161   1.0000
  16.500   1.1012   0.08507   0.07943   0.0015   0.0151   1.0000
  16.750   1.0985   0.08916   0.08367  -0.0001   0.0141   1.0000
  17.000   1.0946   0.09351   0.08814  -0.0019   0.0133   1.0000
  17.250   1.0893   0.09820   0.09293  -0.0040   0.0126   1.0000
  17.500   1.0835   0.10308   0.09792  -0.0062   0.0119   1.0000
  17.750   1.0792   0.10781   0.10279  -0.0085   0.0110   1.0000
  18.000   1.0730   0.11292   0.10802  -0.0110   0.0105   1.0000
  18.250   1.0673   0.11805   0.11326  -0.0136   0.0102   1.0000
  18.500   1.0591   0.12375   0.11905  -0.0167   0.0097   1.0000
  18.750   1.0530   0.12911   0.12454  -0.0196   0.0095   1.0000
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