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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 100,000
Max Cl/Cd: 52.88 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e559-il-100000-n5.txt
Download as CSV file: xf-e559-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 559 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5509   0.08782   0.08198  -0.0626   1.0000   0.0362
 -13.000  -0.5687   0.08161   0.07568  -0.0655   1.0000   0.0365
 -12.750  -0.5832   0.07643   0.07043  -0.0677   1.0000   0.0368
 -12.500  -0.5953   0.07194   0.06588  -0.0694   1.0000   0.0374
 -12.250  -0.6074   0.06766   0.06154  -0.0709   1.0000   0.0380
 -12.000  -0.6178   0.06388   0.05769  -0.0719   1.0000   0.0384
 -11.750  -0.6298   0.06011   0.05385  -0.0728   1.0000   0.0391
 -11.500  -0.6406   0.05677   0.05044  -0.0732   1.0000   0.0397
 -11.250  -0.6524   0.05361   0.04722  -0.0732   1.0000   0.0404
 -11.000  -0.6648   0.05075   0.04429  -0.0727   1.0000   0.0409
 -10.750  -0.6797   0.04813   0.04161  -0.0715   1.0000   0.0414
 -10.500  -0.6996   0.04577   0.03926  -0.0695   1.0000   0.0416
 -10.250  -0.7184   0.04337   0.03686  -0.0680   1.0000   0.0418
 -10.000  -0.7293   0.04072   0.03419  -0.0681   1.0000   0.0424
  -9.750  -0.7130   0.03817   0.03158  -0.0719   0.9956   0.0440
  -9.500  -0.6840   0.03579   0.02902  -0.0767   0.9882   0.0467
  -9.250  -0.6540   0.03352   0.02662  -0.0812   0.9809   0.0503
  -9.000  -0.6242   0.03151   0.02448  -0.0851   0.9729   0.0554
  -8.750  -0.5965   0.02953   0.02245  -0.0883   0.9640   0.0613
  -8.500  -0.5656   0.02774   0.02057  -0.0915   0.9562   0.0702
  -8.250  -0.5341   0.02614   0.01892  -0.0944   0.9480   0.0837
  -8.000  -0.5036   0.02488   0.01758  -0.0965   0.9392   0.0998
  -7.750  -0.4674   0.02377   0.01646  -0.0995   0.9327   0.1176
  -7.500  -0.4368   0.02297   0.01560  -0.1009   0.9232   0.1344
  -7.250  -0.3986   0.02226   0.01480  -0.1036   0.9172   0.1560
  -7.000  -0.3677   0.02180   0.01434  -0.1048   0.9072   0.1755
  -6.750  -0.3289   0.02136   0.01382  -0.1072   0.9014   0.1935
  -6.500  -0.2977   0.02097   0.01332  -0.1080   0.8911   0.2063
  -6.250  -0.2575   0.02051   0.01272  -0.1104   0.8850   0.2199
  -6.000  -0.2254   0.02022   0.01231  -0.1112   0.8741   0.2314
  -5.750  -0.1849   0.01989   0.01191  -0.1136   0.8670   0.2432
  -5.500  -0.1506   0.01958   0.01148  -0.1148   0.8559   0.2541
  -5.250  -0.1139   0.01927   0.01099  -0.1164   0.8458   0.2657
  -5.000  -0.0755   0.01902   0.01069  -0.1183   0.8362   0.2752
  -4.750  -0.0417   0.01876   0.01028  -0.1193   0.8238   0.2851
  -4.500  -0.0062   0.01855   0.00998  -0.1206   0.8122   0.2948
  -4.000   0.0625   0.01817   0.00932  -0.1228   0.7877   0.3137
  -3.750   0.0940   0.01803   0.00912  -0.1234   0.7746   0.3215
  -3.500   0.1265   0.01790   0.00881  -0.1241   0.7621   0.3313
  -3.250   0.1590   0.01778   0.00863  -0.1248   0.7504   0.3389
  -3.000   0.1883   0.01770   0.00841  -0.1250   0.7370   0.3481
  -2.750   0.2172   0.01763   0.00829  -0.1250   0.7245   0.3555
  -2.500   0.2472   0.01756   0.00809  -0.1253   0.7128   0.3645
  -2.250   0.2764   0.01751   0.00797  -0.1254   0.7011   0.3721
  -2.000   0.3041   0.01749   0.00786  -0.1253   0.6889   0.3810
  -1.750   0.3324   0.01746   0.00777  -0.1252   0.6778   0.3887
  -1.500   0.3610   0.01745   0.00765  -0.1252   0.6672   0.3977
  -1.250   0.3879   0.01745   0.00762  -0.1249   0.6557   0.4058
  -1.000   0.4159   0.01746   0.00755  -0.1248   0.6456   0.4148
  -0.750   0.4432   0.01747   0.00752  -0.1246   0.6352   0.4233
  -0.500   0.4702   0.01751   0.00751  -0.1243   0.6250   0.4327
  -0.250   0.4980   0.01754   0.00748  -0.1242   0.6159   0.4415
   0.000   0.5243   0.01760   0.00752  -0.1238   0.6056   0.4516
   0.250   0.5516   0.01765   0.00754  -0.1236   0.5971   0.4607
   0.500   0.5778   0.01773   0.00760  -0.1232   0.5873   0.4714
   0.750   0.6046   0.01780   0.00766  -0.1229   0.5791   0.4814
   1.000   0.6307   0.01788   0.00776  -0.1225   0.5701   0.4922
   1.250   0.6577   0.01799   0.00782  -0.1222   0.5621   0.5044
   1.500   0.6833   0.01808   0.00797  -0.1217   0.5535   0.5159
   1.750   0.7100   0.01819   0.00807  -0.1214   0.5462   0.5288
   2.000   0.7354   0.01832   0.00824  -0.1209   0.5379   0.5426
   2.250   0.7624   0.01845   0.00834  -0.1206   0.5312   0.5581
   2.500   0.7873   0.01859   0.00858  -0.1201   0.5230   0.5745
   2.750   0.8137   0.01872   0.00873  -0.1197   0.5164   0.5925
   3.000   0.8385   0.01888   0.00898  -0.1191   0.5090   0.6129
   3.250   0.8636   0.01902   0.00920  -0.1185   0.5021   0.6368
   3.500   0.8887   0.01916   0.00941  -0.1178   0.4959   0.6643
   4.000   0.9346   0.01940   0.00992  -0.1156   0.4832   0.7397
   4.500   0.9714   0.01943   0.01034  -0.1112   0.4708   0.9056
   4.750   1.0011   0.01966   0.01049  -0.1116   0.4654   1.0000
   5.000   1.0258   0.02004   0.01089  -0.1113   0.4588   1.0000
   5.250   1.0517   0.02038   0.01120  -0.1111   0.4528   1.0000
   5.500   1.0787   0.02073   0.01149  -0.1110   0.4476   1.0000
   5.750   1.1020   0.02114   0.01197  -0.1104   0.4412   1.0000
   6.000   1.1274   0.02151   0.01232  -0.1101   0.4356   1.0000
   6.250   1.1530   0.02189   0.01268  -0.1098   0.4304   1.0000
   6.500   1.1752   0.02234   0.01321  -0.1090   0.4241   1.0000
   6.750   1.1999   0.02273   0.01359  -0.1086   0.4187   1.0000
   7.000   1.2241   0.02315   0.01403  -0.1081   0.4135   1.0000
   7.250   1.2450   0.02363   0.01461  -0.1071   0.4072   1.0000
   7.500   1.2689   0.02403   0.01501  -0.1065   0.4019   1.0000
   7.750   1.2910   0.02450   0.01554  -0.1057   0.3964   1.0000
   8.000   1.3106   0.02501   0.01616  -0.1045   0.3901   1.0000
   8.250   1.3338   0.02542   0.01656  -0.1038   0.3848   1.0000
   8.500   1.3527   0.02596   0.01721  -0.1025   0.3790   1.0000
   8.750   1.3708   0.02648   0.01784  -0.1011   0.3727   1.0000
   9.000   1.3938   0.02689   0.01822  -0.1004   0.3675   1.0000
   9.250   1.4072   0.02754   0.01904  -0.0984   0.3609   1.0000
   9.500   1.4241   0.02805   0.01964  -0.0968   0.3547   1.0000
   9.750   1.4418   0.02854   0.02016  -0.0953   0.3491   1.0000
  10.000   1.4502   0.02924   0.02102  -0.0925   0.3422   1.0000
  10.250   1.4660   0.02972   0.02152  -0.0908   0.3362   1.0000
  10.500   1.4736   0.03051   0.02245  -0.0880   0.3295   1.0000
  10.750   1.4831   0.03120   0.02325  -0.0856   0.3227   1.0000
  11.000   1.4930   0.03194   0.02405  -0.0833   0.3162   1.0000
  11.250   1.4971   0.03294   0.02520  -0.0806   0.3089   1.0000
  11.500   1.5074   0.03369   0.02597  -0.0786   0.3024   1.0000
  11.750   1.5067   0.03507   0.02754  -0.0757   0.2947   1.0000
  12.000   1.5148   0.03599   0.02847  -0.0738   0.2879   1.0000
  12.250   1.5112   0.03778   0.03048  -0.0712   0.2799   1.0000
  12.500   1.5158   0.03906   0.03177  -0.0694   0.2727   1.0000
  12.750   1.5103   0.04128   0.03419  -0.0673   0.2646   1.0000
  13.000   1.5124   0.04294   0.03584  -0.0658   0.2571   1.0000
  13.250   1.5042   0.04575   0.03886  -0.0643   0.2487   1.0000
  13.500   1.5023   0.04803   0.04117  -0.0632   0.2409   1.0000
  13.750   1.4927   0.05135   0.04465  -0.0624   0.2323   1.0000
  14.000   1.4868   0.05440   0.04776  -0.0618   0.2243   1.0000
  14.250   1.4768   0.05813   0.05160  -0.0616   0.2158   1.0000
  14.500   1.4671   0.06201   0.05559  -0.0616   0.2077   1.0000
  14.750   1.4580   0.06597   0.05959  -0.0619   0.1993   1.0000
  15.000   1.4454   0.07068   0.06443  -0.0626   0.1912   1.0000
  15.250   1.4382   0.07464   0.06837  -0.0631   0.1831   1.0000
  15.500   1.4234   0.08007   0.07395  -0.0644   0.1749   1.0000
  15.750   1.4156   0.08443   0.07831  -0.0654   0.1672   1.0000
  16.000   1.4032   0.08974   0.08373  -0.0669   0.1594   1.0000
  16.250   1.3951   0.09442   0.08843  -0.0682   0.1520   1.0000
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