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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 50,000
Max Cl/Cd: 4.75 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e554-il-50000.txt
Download as CSV file: xf-e554-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 554 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4675   0.09661   0.08984  -0.0573   1.0000   0.1150
 -11.500  -0.4631   0.09300   0.08627  -0.0572   1.0000   0.1168
 -11.250  -0.6067   0.07541   0.06848  -0.0712   1.0000   0.1009
 -11.000  -0.6236   0.07118   0.06422  -0.0714   1.0000   0.1002
 -10.750  -0.6459   0.06754   0.06055  -0.0706   1.0000   0.0997
 -10.500  -0.6679   0.06446   0.05742  -0.0689   1.0000   0.0992
 -10.250  -0.6859   0.06129   0.05415  -0.0672   1.0000   0.0988
 -10.000  -0.7012   0.05830   0.05101  -0.0651   1.0000   0.0986
  -9.750  -0.7132   0.05552   0.04805  -0.0627   1.0000   0.0987
  -9.500  -0.7234   0.05302   0.04533  -0.0600   1.0000   0.0993
  -9.250  -0.7326   0.05082   0.04285  -0.0571   1.0000   0.1002
  -9.000  -0.7338   0.04847   0.04042  -0.0545   1.0000   0.1025
  -8.750  -0.7276   0.04673   0.03878  -0.0521   1.0000   0.1062
  -8.500  -0.7273   0.04511   0.03703  -0.0494   1.0000   0.1096
  -8.250  -0.7273   0.04351   0.03514  -0.0468   1.0000   0.1130
  -8.000  -0.7187   0.04194   0.03369  -0.0445   1.0000   0.1188
  -7.750  -0.7132   0.04068   0.03231  -0.0423   1.0000   0.1265
  -7.500  -0.7043   0.03950   0.03134  -0.0398   1.0000   0.1353
  -7.250  -0.6975   0.03832   0.03024  -0.0373   1.0000   0.1476
  -7.000  -0.6922   0.03716   0.02923  -0.0349   1.0000   0.1627
  -6.750  -0.6761   0.03530   0.02774  -0.0350   0.9957   0.1938
  -6.500  -0.6450   0.03417   0.02882  -0.0365   0.9825   0.3504
  -6.250  -0.5768   0.04863   0.04320  -0.0252   0.9641   0.4572
  -6.000  -0.4698   0.06084   0.05491  -0.0163   0.9531   0.5071
  -5.750  -0.3628   0.06499   0.05849  -0.0174   0.9451   0.5633
  -5.500  -0.2198   0.06631   0.05922  -0.0242   0.9408   0.6537
  -2.750   0.1105   0.05231   0.04343  -0.0536   0.8250   0.7779
  -2.500   0.0900   0.05277   0.04391  -0.0484   0.8134   0.7713
  -2.250   0.0674   0.05263   0.04373  -0.0436   0.8062   0.7635
  -2.000  -0.0861   0.05482   0.04623  -0.0196   0.7944   0.7491
  -1.750  -0.0620   0.05406   0.04535  -0.0212   0.7890   0.7522
  -1.500  -0.1303   0.05439   0.04577  -0.0108   0.7834   0.7498
  -1.250  -0.1468   0.05418   0.04554  -0.0074   0.7786   0.7512
  -1.000  -0.1352   0.05379   0.04506  -0.0077   0.7735   0.7544
  -0.750  -0.1229   0.05353   0.04470  -0.0084   0.7691   0.7580
  -0.500  -0.1326   0.05357   0.04468  -0.0071   0.7664   0.7606
  -0.250  -0.1300   0.05370   0.04478  -0.0060   0.7637   0.7633
   0.000  -0.1209   0.05389   0.04492  -0.0058   0.7607   0.7671
   0.250  -0.1065   0.05415   0.04511  -0.0066   0.7581   0.7715
   0.500  -0.0899   0.05453   0.04540  -0.0084   0.7567   0.7756
   0.750  -0.0716   0.05500   0.04581  -0.0100   0.7552   0.7795
   1.000  -0.0648   0.05559   0.04638  -0.0097   0.7559   0.7837
   1.250  -0.0647   0.05637   0.04715  -0.0094   0.7611   0.7881
   1.500  -0.0485   0.05737   0.04810  -0.0115   0.7665   0.7930
   1.750  -0.0233   0.05855   0.04923  -0.0139   0.7703   0.7977
   2.000  -0.1629   0.05759   0.04860  -0.0003   0.9312   0.7969
   2.250  -0.1399   0.05852   0.04948  -0.0020   0.9228   0.8022
   2.500  -0.1027   0.06043   0.05130  -0.0064   0.9120   0.8093
   2.750  -0.0839   0.06082   0.05166  -0.0075   0.8999   0.8150
   3.000  -0.0545   0.06263   0.05342  -0.0102   0.8927   0.8219
   3.250  -0.0262   0.06372   0.05447  -0.0132   0.8795   0.8286
   3.500  -0.0097   0.06441   0.05515  -0.0134   0.8678   0.8351
   3.750   0.0311   0.06734   0.05803  -0.0181   0.8593   0.8450
   4.000   0.0403   0.06715   0.05787  -0.0172   0.8461   0.8522
   4.250   0.0622   0.06853   0.05923  -0.0188   0.8360   0.8614
   4.500   0.0940   0.07062   0.06135  -0.0214   0.8250   0.8723
   4.750   0.1051   0.07102   0.06178  -0.0211   0.8125   0.8824
   5.000   0.1366   0.07359   0.06439  -0.0238   0.8051   0.8974
   5.250   0.1538   0.07425   0.06512  -0.0244   0.7908   0.9125
   5.500   0.1695   0.07523   0.06619  -0.0253   0.7788   0.9302
   5.750   0.2176   0.07876   0.06983  -0.0318   0.7697   0.9652
   6.000   0.2388   0.07976   0.07085  -0.0345   0.7547   1.0000
   6.250   0.2573   0.08132   0.07241  -0.0372   0.7419   1.0000
   6.500   0.3037   0.08554   0.07660  -0.0439   0.7339   1.0000
   6.750   0.3251   0.08710   0.07817  -0.0467   0.7194   1.0000
   7.000   0.3416   0.08896   0.08003  -0.0490   0.7068   1.0000
   7.250   0.3898   0.09374   0.08477  -0.0553   0.6988   1.0000
   7.500   0.4022   0.09495   0.08598  -0.0567   0.6841   1.0000
   7.750   0.4137   0.09691   0.08794  -0.0581   0.6720   1.0000
   8.000   0.4622   0.10208   0.09308  -0.0633   0.6638   1.0000
   8.250   0.4634   0.10275   0.09377  -0.0631   0.6492   1.0000
   8.500   0.4718   0.10488   0.09590  -0.0639   0.6378   1.0000
   8.750   0.5166   0.10991   0.10094  -0.0677   0.6289   1.0000
   9.000   0.5122   0.11054   0.10158  -0.0670   0.6148   1.0000
   9.250   0.5206   0.11304   0.10410  -0.0677   0.6046   1.0000
   9.500   0.5585   0.11750   0.10861  -0.0703   0.5943   1.0000
   9.750   0.5529   0.11851   0.10965  -0.0698   0.5812   1.0000
  10.000   0.5662   0.12168   0.11285  -0.0709   0.5724   1.0000
  10.250   0.5927   0.12517   0.11639  -0.0724   0.5603   1.0000
  10.500   0.5893   0.12684   0.11811  -0.0724   0.5484   1.0000
  10.750   0.6184   0.13152   0.12285  -0.0742   0.5407   1.0000
  11.000   0.6225   0.13316   0.12455  -0.0744   0.5271   1.0000
  11.250   0.6236   0.13563   0.12706  -0.0750   0.5173   1.0000
  11.500   0.6635   0.14112   0.13266  -0.0769   0.5074   1.0000
  11.750   0.6492   0.14158   0.13315  -0.0768   0.4953   1.0000
  12.000   0.6646   0.14551   0.13715  -0.0780   0.4879   1.0000
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