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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 50,000
Max Cl/Cd: 11.87 at α=-1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e584-il-50000-n5.txt
Download as CSV file: xf-e584-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1851   0.11044   0.10399  -0.0853   0.9347   0.0517
 -10.250  -0.1707   0.10575   0.09927  -0.0892   0.9297   0.0494
 -10.000  -0.1785   0.09842   0.09199  -0.0963   0.9210   0.0454
  -9.750  -0.1637   0.09424   0.08775  -0.0997   0.9156   0.0444
  -9.500  -0.1561   0.08967   0.08316  -0.1035   0.9087   0.0435
  -9.250  -0.1533   0.08453   0.07800  -0.1082   0.9010   0.0425
  -9.000  -0.1567   0.07868   0.07210  -0.1135   0.8937   0.0416
  -8.750  -0.1696   0.07415   0.06749  -0.1160   0.8840   0.0407
  -8.500  -0.1911   0.07036   0.06357  -0.1159   0.8741   0.0398
  -8.250  -0.2218   0.06648   0.05935  -0.1139   0.8644   0.0386
  -8.000  -0.2321   0.06461   0.05737  -0.1110   0.8558   0.0384
  -7.750  -0.2385   0.06199   0.05454  -0.1090   0.8492   0.0383
  -7.500  -0.2422   0.05952   0.05183  -0.1068   0.8434   0.0381
  -7.250  -0.2509   0.05794   0.05005  -0.1029   0.8355   0.0380
  -7.000  -0.2485   0.05514   0.04690  -0.1010   0.8308   0.0379
  -6.750  -0.2511   0.05326   0.04471  -0.0976   0.8246   0.0379
  -6.500  -0.2532   0.05158   0.04274  -0.0939   0.8184   0.0380
  -6.250  -0.2448   0.04900   0.03958  -0.0917   0.8143   0.0386
  -6.000  -0.2233   0.04724   0.03772  -0.0918   0.8116   0.0403
  -5.750  -0.2310   0.04686   0.03719  -0.0867   0.8037   0.0411
  -5.500  -0.2162   0.04517   0.03511  -0.0850   0.7995   0.0430
  -5.250  -0.1925   0.04309   0.03244  -0.0842   0.7966   0.0449
  -5.000  -0.1628   0.04126   0.03038  -0.0847   0.7945   0.0467
  -4.750  -0.1704   0.04136   0.03042  -0.0793   0.7867   0.0478
  -4.500  -0.1468   0.04030   0.02905  -0.0785   0.7830   0.0521
  -4.250  -0.1158   0.03913   0.02779  -0.0789   0.7804   0.0577
  -4.000  -0.0792   0.03799   0.02650  -0.0800   0.7784   0.0664
  -3.750  -0.0831   0.03834   0.02675  -0.0750   0.7715   0.0711
  -3.500  -0.0648   0.03789   0.02626  -0.0734   0.7671   0.0828
  -3.250  -0.0398   0.03709   0.02551  -0.0730   0.7641   0.1039
  -3.000  -0.0136   0.03600   0.02465  -0.0728   0.7618   0.1486
  -2.750  -0.0274   0.03650   0.02531  -0.0667   0.7542   0.1716
  -2.500   0.0144   0.03538   0.02724  -0.0642   0.7528   0.7321
  -2.000   0.3411   0.03510   0.02493  -0.1068   0.7606   0.9781
  -1.750   0.3668   0.03568   0.02536  -0.1085   0.7539   0.9918
  -1.500   0.4066   0.03564   0.02506  -0.1121   0.7501   1.0000
  -1.250   0.4251   0.03580   0.02505  -0.1112   0.7465   1.0000
  -1.000   0.4211   0.03671   0.02588  -0.1068   0.7403   1.0000
  -0.750   0.4149   0.03766   0.02678  -0.1021   0.7335   1.0000
  -0.500   0.4340   0.03786   0.02682  -0.1011   0.7300   1.0000
  -0.250   0.4189   0.03908   0.02800  -0.0951   0.7224   1.0000
   0.000   0.4166   0.03985   0.02870  -0.0909   0.7163   1.0000
   0.250   0.4401   0.03998   0.02868  -0.0905   0.7132   1.0000
   0.500   0.4060   0.04165   0.03039  -0.0818   0.7034   1.0000
   0.750   0.4220   0.04198   0.03060  -0.0803   0.6993   1.0000
   1.000   0.4376   0.04233   0.03085  -0.0788   0.6954   1.0000
   1.250   0.4159   0.04374   0.03225  -0.0722   0.6862   1.0000
   1.500   0.4385   0.04390   0.03230  -0.0716   0.6830   1.0000
   1.750   0.4187   0.04529   0.03369  -0.0654   0.6740   1.0000
   2.000   0.4357   0.04562   0.03393  -0.0640   0.6698   1.0000
   2.250   0.4618   0.04570   0.03391  -0.0638   0.6671   1.0000
   2.500   0.4371   0.04724   0.03547  -0.0572   0.6569   1.0000
   2.750   0.4609   0.04739   0.03553  -0.0566   0.6537   1.0000
   3.000   0.4412   0.04882   0.03697  -0.0508   0.6441   1.0000
   3.250   0.4608   0.04907   0.03716  -0.0496   0.6401   1.0000
   3.500   0.4471   0.05032   0.03841  -0.0447   0.6313   1.0000
   3.750   0.4620   0.05071   0.03875  -0.0431   0.6266   1.0000
   4.000   0.4545   0.05177   0.03981  -0.0390   0.6184   1.0000
   4.250   0.4657   0.05228   0.04028  -0.0370   0.6130   1.0000
   4.750   0.4736   0.05381   0.04177  -0.0316   0.5993   1.0000
   5.000   0.4991   0.05394   0.04188  -0.0313   0.5961   1.0000
   5.250   0.4889   0.05542   0.04337  -0.0278   0.5857   1.0000
   5.500   0.5156   0.05559   0.04353  -0.0277   0.5822   1.0000
   5.750   0.5104   0.05718   0.04512  -0.0251   0.5721   1.0000
   6.000   0.5371   0.05739   0.04533  -0.0251   0.5681   1.0000
   6.250   0.5366   0.05898   0.04695  -0.0233   0.5584   1.0000
   6.500   0.5613   0.05934   0.04735  -0.0232   0.5536   1.0000
   6.750   0.5662   0.06079   0.04883  -0.0220   0.5446   1.0000
   7.000   0.5873   0.06140   0.04946  -0.0218   0.5388   1.0000
   7.250   0.6184   0.06139   0.04948  -0.0221   0.5353   1.0000
   7.500   0.6153   0.06347   0.05161  -0.0207   0.5239   1.0000
   7.750   0.6461   0.06347   0.05169  -0.0210   0.5203   1.0000
   8.000   0.6444   0.06558   0.05386  -0.0198   0.5088   1.0000
   8.250   0.6745   0.06558   0.05392  -0.0201   0.5049   1.0000
   8.500   0.6740   0.06772   0.05613  -0.0191   0.4935   1.0000
   8.750   0.7046   0.06764   0.05614  -0.0193   0.4895   1.0000
   9.000   0.7034   0.06997   0.05855  -0.0185   0.4780   1.0000
   9.250   0.7347   0.06974   0.05842  -0.0187   0.4740   1.0000
   9.500   0.7331   0.07222   0.06098  -0.0180   0.4621   1.0000
   9.750   0.7651   0.07184   0.06072  -0.0181   0.4582   1.0000
  10.000   0.7626   0.07451   0.06348  -0.0175   0.4460   1.0000
  10.250   0.7951   0.07397   0.06307  -0.0175   0.4422   1.0000
  10.500   0.7919   0.07683   0.06602  -0.0170   0.4297   1.0000
  10.750   0.8231   0.07631   0.06564  -0.0169   0.4256   1.0000
  11.000   0.8212   0.07912   0.06855  -0.0166   0.4131   1.0000
  11.500   0.8504   0.08139   0.07109  -0.0162   0.3966   1.0000
  12.000   0.8801   0.08352   0.07349  -0.0157   0.3800   1.0000
  12.250   0.8772   0.08678   0.07687  -0.0157   0.3675   1.0000
  12.500   0.9099   0.08555   0.07582  -0.0152   0.3635   1.0000
  12.750   0.9047   0.08921   0.07959  -0.0154   0.3504   1.0000
  13.000   0.9389   0.08750   0.07806  -0.0147   0.3466   1.0000
  13.250   0.9331   0.09135   0.08203  -0.0150   0.3336   1.0000
  13.750   0.9629   0.09313   0.08414  -0.0146   0.3168   1.0000
  14.250   0.9605   0.09993   0.09118  -0.0155   0.2938   1.0000
  14.500   0.9851   0.09916   0.09062  -0.0148   0.2868   1.0000
  15.000   1.0192   0.10004   0.09182  -0.0142   0.2699   1.0000
  15.250   1.0061   0.10554   0.09742  -0.0156   0.2571   1.0000
  15.750   1.0420   0.10595   0.09817  -0.0149   0.2397   1.0000
  16.750   1.0424   0.11946   0.11215  -0.0186   0.1983   1.0000
  17.000   1.0663   0.11835   0.11118  -0.0178   0.1896   1.0000
  17.250   1.0826   0.11865   0.11159  -0.0177   0.1798   1.0000
  17.500   1.0512   0.12835   0.12138  -0.0217   0.1701   1.0000
  17.750   1.0803   0.12602   0.11915  -0.0204   0.1611   1.0000
  18.000   1.0799   0.12961   0.12285  -0.0219   0.1519   1.0000
  18.250   1.0544   0.13863   0.13195  -0.0261   0.1441   1.0000
  18.500   1.0927   0.13405   0.12742  -0.0237   0.1344   1.0000
  18.750   1.0399   0.14947   0.14292  -0.0314   0.1283   1.0000
  19.000   1.0722   0.14584   0.13939  -0.0295   0.1200   1.0000
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