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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 500,000
Max Cl/Cd: 100.12 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e558-il-500000.txt
Download as CSV file: xf-e558-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 558 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.6059   0.13866   0.13588  -0.0318   1.0000   0.0146
 -17.000  -0.6657   0.12112   0.11808  -0.0409   1.0000   0.0141
 -16.750  -0.7007   0.11003   0.10678  -0.0468   1.0000   0.0138
 -16.500  -0.7211   0.10234   0.09894  -0.0509   1.0000   0.0137
 -16.250  -0.7386   0.09545   0.09192  -0.0546   1.0000   0.0138
 -16.000  -0.7529   0.08944   0.08578  -0.0576   1.0000   0.0137
 -15.750  -0.7617   0.08448   0.08071  -0.0601   1.0000   0.0138
 -15.500  -0.7705   0.07972   0.07584  -0.0624   1.0000   0.0138
 -15.250  -0.7777   0.07539   0.07141  -0.0643   1.0000   0.0137
 -15.000  -0.7843   0.07121   0.06714  -0.0663   1.0000   0.0139
 -14.750  -0.7886   0.06765   0.06350  -0.0675   1.0000   0.0138
 -14.500  -0.7931   0.06414   0.05990  -0.0689   1.0000   0.0139
 -14.250  -0.7997   0.06050   0.05618  -0.0703   1.0000   0.0142
 -14.000  -0.8023   0.05761   0.05322  -0.0710   1.0000   0.0141
 -13.750  -0.8065   0.05455   0.05009  -0.0717   1.0000   0.0142
 -13.500  -0.8113   0.05146   0.04692  -0.0725   1.0000   0.0144
 -13.250  -0.8149   0.04873   0.04414  -0.0728   1.0000   0.0144
 -13.000  -0.8188   0.04602   0.04136  -0.0731   1.0000   0.0145
 -12.750  -0.8233   0.04335   0.03863  -0.0732   1.0000   0.0145
 -12.500  -0.8288   0.04066   0.03588  -0.0733   1.0000   0.0147
 -12.250  -0.8352   0.03809   0.03325  -0.0730   1.0000   0.0147
 -12.000  -0.8433   0.03558   0.03067  -0.0724   1.0000   0.0148
 -11.750  -0.8565   0.03309   0.02811  -0.0713   1.0000   0.0149
 -11.500  -0.8800   0.03060   0.02556  -0.0691   1.0000   0.0149
 -11.250  -0.8854   0.02856   0.02341  -0.0684   1.0000   0.0150
 -11.000  -0.8652   0.02649   0.02126  -0.0711   0.9974   0.0152
 -10.750  -0.8322   0.02439   0.01910  -0.0758   0.9937   0.0157
 -10.500  -0.8008   0.02291   0.01756  -0.0788   0.9893   0.0162
 -10.250  -0.7665   0.02165   0.01623  -0.0819   0.9857   0.0168
 -10.000  -0.7296   0.02053   0.01501  -0.0852   0.9832   0.0175
  -9.750  -0.6997   0.01947   0.01387  -0.0868   0.9776   0.0183
  -9.500  -0.6658   0.01820   0.01255  -0.0895   0.9735   0.0194
  -9.250  -0.6282   0.01735   0.01164  -0.0923   0.9712   0.0210
  -9.000  -0.6012   0.01637   0.01060  -0.0929   0.9632   0.0225
  -8.750  -0.5650   0.01552   0.00970  -0.0952   0.9597   0.0253
  -8.500  -0.5369   0.01459   0.00875  -0.0958   0.9515   0.0301
  -8.250  -0.5036   0.01337   0.00764  -0.0978   0.9464   0.0487
  -8.000  -0.4754   0.01249   0.00689  -0.0983   0.9375   0.0728
  -7.750  -0.4395   0.01177   0.00626  -0.1003   0.9318   0.0957
  -7.500  -0.4042   0.01116   0.00574  -0.1021   0.9231   0.1180
  -7.250  -0.3602   0.01062   0.00527  -0.1057   0.9162   0.1411
  -7.000  -0.3177   0.01022   0.00489  -0.1088   0.9051   0.1617
  -6.750  -0.2746   0.00992   0.00455  -0.1120   0.8913   0.1798
  -6.500  -0.2370   0.00967   0.00429  -0.1140   0.8732   0.1983
  -6.250  -0.2044   0.00953   0.00410  -0.1149   0.8534   0.2154
  -6.000  -0.1748   0.00947   0.00395  -0.1151   0.8335   0.2298
  -5.750  -0.1468   0.00943   0.00383  -0.1150   0.8141   0.2414
  -5.500  -0.1197   0.00938   0.00370  -0.1147   0.7961   0.2513
  -5.250  -0.0925   0.00939   0.00358  -0.1144   0.7790   0.2600
  -5.000  -0.0660   0.00932   0.00347  -0.1140   0.7626   0.2685
  -4.750  -0.0390   0.00934   0.00336  -0.1136   0.7468   0.2768
  -4.500  -0.0124   0.00929   0.00327  -0.1133   0.7322   0.2848
  -4.250   0.0146   0.00932   0.00318  -0.1129   0.7180   0.2928
  -4.000   0.0412   0.00927   0.00309  -0.1125   0.7038   0.3004
  -3.750   0.0683   0.00928   0.00303  -0.1122   0.6900   0.3083
  -3.500   0.0953   0.00927   0.00295  -0.1119   0.6773   0.3157
  -3.250   0.1221   0.00928   0.00290  -0.1115   0.6649   0.3232
  -3.000   0.1494   0.00930   0.00284  -0.1112   0.6521   0.3304
  -2.750   0.1764   0.00928   0.00280  -0.1110   0.6401   0.3379
  -2.500   0.2036   0.00934   0.00276  -0.1106   0.6288   0.3453
  -2.250   0.2307   0.00931   0.00273  -0.1104   0.6173   0.3523
  -2.000   0.2580   0.00935   0.00271  -0.1101   0.6063   0.3600
  -1.750   0.2849   0.00939   0.00268  -0.1098   0.5954   0.3670
  -1.500   0.3123   0.00938   0.00267  -0.1096   0.5850   0.3743
  -1.250   0.3396   0.00947   0.00267  -0.1093   0.5752   0.3818
  -1.000   0.3668   0.00945   0.00266  -0.1091   0.5649   0.3891
  -0.750   0.3940   0.00951   0.00267  -0.1088   0.5554   0.3967
  -0.500   0.4212   0.00954   0.00268  -0.1086   0.5458   0.4044
  -0.250   0.4484   0.00958   0.00271  -0.1083   0.5372   0.4123
   0.000   0.4757   0.00965   0.00272  -0.1081   0.5281   0.4198
   0.250   0.5027   0.00967   0.00276  -0.1078   0.5196   0.4282
   0.500   0.5299   0.00975   0.00279  -0.1076   0.5108   0.4367
   0.750   0.5569   0.00979   0.00285  -0.1073   0.5032   0.4450
   1.000   0.5841   0.00985   0.00290  -0.1071   0.4951   0.4542
   1.250   0.6107   0.00993   0.00296  -0.1068   0.4876   0.4635
   1.500   0.6382   0.00998   0.00302  -0.1066   0.4799   0.4735
   1.750   0.6646   0.01006   0.00310  -0.1063   0.4726   0.4835
   2.000   0.6919   0.01011   0.00319  -0.1061   0.4660   0.4949
   2.250   0.7187   0.01018   0.00327  -0.1058   0.4591   0.5070
   2.500   0.7451   0.01028   0.00338  -0.1055   0.4526   0.5195
   2.750   0.7722   0.01032   0.00348  -0.1052   0.4460   0.5339
   3.000   0.7985   0.01042   0.00359  -0.1049   0.4397   0.5504
   3.250   0.8250   0.01050   0.00373  -0.1046   0.4340   0.5687
   3.500   0.8517   0.01054   0.00386  -0.1043   0.4279   0.5900
   3.750   0.8774   0.01065   0.00400  -0.1039   0.4219   0.6155
   4.000   0.9035   0.01071   0.00417  -0.1035   0.4164   0.6454
   4.250   0.9295   0.01074   0.00433  -0.1030   0.4109   0.6808
   4.500   0.9542   0.01081   0.00450  -0.1024   0.4054   0.7247
   4.750   0.9780   0.01084   0.00471  -0.1015   0.4002   0.7799
   5.000   0.9990   0.01077   0.00488  -0.0998   0.3951   0.8537
   5.250   1.0266   0.01073   0.00497  -0.0995   0.3896   1.0000
   5.500   1.0523   0.01096   0.00516  -0.0992   0.3843   1.0000
   5.750   1.0787   0.01109   0.00532  -0.0989   0.3791   1.0000
   6.000   1.1041   0.01129   0.00549  -0.0985   0.3737   1.0000
   6.250   1.1289   0.01157   0.00572  -0.0979   0.3685   1.0000
   6.500   1.1547   0.01170   0.00590  -0.0976   0.3636   1.0000
   6.750   1.1797   0.01189   0.00609  -0.0970   0.3583   1.0000
   7.000   1.2036   0.01217   0.00633  -0.0964   0.3530   1.0000
   7.250   1.2285   0.01234   0.00655  -0.0958   0.3479   1.0000
   7.500   1.2528   0.01253   0.00675  -0.0952   0.3423   1.0000
   7.750   1.2754   0.01282   0.00701  -0.0943   0.3366   1.0000
   8.000   1.2995   0.01301   0.00725  -0.0937   0.3314   1.0000
   8.250   1.3226   0.01321   0.00748  -0.0928   0.3255   1.0000
   8.500   1.3438   0.01354   0.00777  -0.0917   0.3197   1.0000
   8.750   1.3668   0.01372   0.00802  -0.0909   0.3142   1.0000
   9.000   1.3874   0.01396   0.00828  -0.0896   0.3081   1.0000
   9.250   1.4058   0.01428   0.00859  -0.0880   0.3015   1.0000
   9.500   1.4259   0.01449   0.00885  -0.0867   0.2938   1.0000
   9.750   1.4422   0.01488   0.00921  -0.0847   0.2866   1.0000
  10.000   1.4627   0.01512   0.00952  -0.0835   0.2791   1.0000
  10.250   1.4777   0.01556   0.00992  -0.0815   0.2707   1.0000
  10.500   1.4968   0.01587   0.01029  -0.0801   0.2623   1.0000
  10.750   1.5116   0.01635   0.01075  -0.0781   0.2533   1.0000
  11.000   1.5273   0.01680   0.01122  -0.0764   0.2438   1.0000
  11.250   1.5416   0.01733   0.01176  -0.0744   0.2340   1.0000
  11.500   1.5527   0.01801   0.01241  -0.0722   0.2223   1.0000
  11.750   1.5622   0.01880   0.01316  -0.0698   0.2099   1.0000
  12.000   1.5715   0.01963   0.01398  -0.0675   0.1969   1.0000
  12.250   1.5787   0.02061   0.01494  -0.0651   0.1842   1.0000
  12.500   1.5843   0.02174   0.01605  -0.0627   0.1723   1.0000
  12.750   1.5877   0.02305   0.01735  -0.0603   0.1608   1.0000
  13.000   1.5892   0.02459   0.01886  -0.0579   0.1496   1.0000
  13.250   1.5893   0.02633   0.02059  -0.0557   0.1387   1.0000
  13.500   1.5902   0.02814   0.02240  -0.0539   0.1284   1.0000
  13.750   1.5892   0.03022   0.02449  -0.0522   0.1193   1.0000
  14.000   1.5855   0.03265   0.02692  -0.0507   0.1108   1.0000
  14.250   1.5821   0.03521   0.02950  -0.0495   0.1023   1.0000
  14.500   1.5785   0.03794   0.03226  -0.0486   0.0952   1.0000
  14.750   1.5709   0.04120   0.03554  -0.0479   0.0882   1.0000
  15.000   1.5666   0.04427   0.03866  -0.0475   0.0821   1.0000
  15.250   1.5577   0.04798   0.04240  -0.0473   0.0768   1.0000
  15.500   1.5517   0.05148   0.04597  -0.0473   0.0713   1.0000
  15.750   1.5408   0.05572   0.05024  -0.0475   0.0667   1.0000
  16.000   1.5341   0.05958   0.05418  -0.0480   0.0621   1.0000
  16.250   1.5224   0.06421   0.05885  -0.0487   0.0582   1.0000
  16.500   1.5143   0.06850   0.06321  -0.0495   0.0540   1.0000
  16.750   1.5018   0.07351   0.06827  -0.0506   0.0505   1.0000
  17.000   1.4927   0.07817   0.07301  -0.0518   0.0468   1.0000
  17.250   1.4799   0.08347   0.07836  -0.0533   0.0434   1.0000
  17.500   1.4696   0.08852   0.08348  -0.0548   0.0398   1.0000
  17.750   1.4567   0.09407   0.08909  -0.0566   0.0369   1.0000
  18.000   1.4460   0.09936   0.09446  -0.0584   0.0335   1.0000
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