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EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 555 AIRFOIL (e555-il)
Reynolds number: 50,000
Max Cl/Cd: 27.83 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e555-il-50000.txt
Download as CSV file: xf-e555-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 555 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4933   0.10227   0.09524  -0.0544   1.0000   0.1134
 -11.250  -0.4838   0.09952   0.09252  -0.0532   1.0000   0.1153
 -11.000  -0.5977   0.08126   0.07425  -0.0676   1.0000   0.0983
 -10.750  -0.6134   0.07647   0.06947  -0.0683   1.0000   0.0974
 -10.500  -0.6359   0.07217   0.06515  -0.0685   1.0000   0.0964
 -10.250  -0.6609   0.06868   0.06165  -0.0676   1.0000   0.0955
 -10.000  -0.6861   0.06548   0.05840  -0.0661   1.0000   0.0946
  -9.750  -0.7062   0.06212   0.05491  -0.0644   1.0000   0.0939
  -9.500  -0.7217   0.05886   0.05147  -0.0625   1.0000   0.0933
  -9.250  -0.7318   0.05571   0.04808  -0.0606   1.0000   0.0931
  -9.000  -0.7368   0.05273   0.04483  -0.0587   1.0000   0.0939
  -8.750  -0.7376   0.04989   0.04166  -0.0568   1.0000   0.0954
  -8.500  -0.7354   0.04721   0.03855  -0.0550   1.0000   0.0976
  -8.250  -0.7253   0.04436   0.03549  -0.0534   1.0000   0.1005
  -8.000  -0.7094   0.04208   0.03323  -0.0515   1.0000   0.1053
  -7.750  -0.6968   0.04007   0.03087  -0.0497   1.0000   0.1120
  -7.500  -0.6798   0.03817   0.02917  -0.0473   1.0000   0.1218
  -7.250  -0.6648   0.03652   0.02763  -0.0447   1.0000   0.1349
  -7.000  -0.6532   0.03486   0.02609  -0.0420   1.0000   0.1538
  -6.750  -0.6454   0.03293   0.02452  -0.0395   1.0000   0.1796
  -6.500  -0.6404   0.03003   0.02232  -0.0383   1.0000   0.2329
  -6.250  -0.6348   0.03321   0.02723  -0.0304   1.0000   0.4164
  -6.000  -0.6237   0.03961   0.03356  -0.0193   1.0000   0.4646
  -5.750  -0.6084   0.04547   0.03935  -0.0077   1.0000   0.4912
  -5.500  -0.5922   0.04939   0.04314   0.0013   1.0000   0.5175
  -5.250  -0.5846   0.05058   0.04415   0.0065   1.0000   0.5456
  -5.000  -0.5602   0.05366   0.04707   0.0150   1.0000   0.5706
  -4.750  -0.5598   0.05315   0.04646   0.0183   1.0000   0.5936
  -4.500  -0.5379   0.05433   0.04748   0.0240   1.0000   0.6174
  -4.250  -0.5302   0.05399   0.04701   0.0275   1.0000   0.6374
  -4.000  -0.5257   0.05332   0.04624   0.0305   1.0000   0.6551
  -3.750  -0.5200   0.05256   0.04537   0.0333   1.0000   0.6706
  -3.500  -0.5151   0.05162   0.04434   0.0356   1.0000   0.6836
  -3.250  -0.5176   0.05019   0.04283   0.0371   1.0000   0.6939
  -3.000  -0.5094   0.04928   0.04181   0.0388   1.0000   0.7035
  -2.750  -0.5049   0.04799   0.04040   0.0395   1.0000   0.7112
  -2.500  -0.4958   0.04701   0.03931   0.0403   1.0000   0.7185
  -2.250  -0.4872   0.04570   0.03787   0.0392   1.0000   0.7249
  -2.000  -0.4751   0.04492   0.03700   0.0401   1.0000   0.7305
  -1.750  -0.4441   0.04448   0.03638   0.0360   0.9940   0.7366
  -1.500  -0.4008   0.04430   0.03598   0.0299   0.9816   0.7427
  -1.250  -0.3629   0.04415   0.03567   0.0257   0.9700   0.7479
  -1.000  -0.3235   0.04395   0.03528   0.0204   0.9581   0.7533
  -0.750  -0.2842   0.04377   0.03494   0.0152   0.9464   0.7578
  -0.500  -0.2544   0.04355   0.03463   0.0128   0.9345   0.7621
  -0.250  -0.2215   0.04345   0.03441   0.0094   0.9227   0.7672
   0.000  -0.1821   0.04346   0.03428   0.0043   0.9110   0.7719
   0.250  -0.1437   0.04359   0.03433   0.0009   0.8998   0.7765
   0.500  -0.1188   0.04354   0.03422  -0.0008   0.8881   0.7815
   0.750  -0.0857   0.04366   0.03426  -0.0043   0.8759   0.7867
   1.000  -0.0515   0.04386   0.03441  -0.0072   0.8650   0.7914
   1.250  -0.0170   0.04410   0.03460  -0.0099   0.8537   0.7974
   1.500   0.0086   0.04435   0.03481  -0.0120   0.8417   0.8032
   1.750   0.0359   0.04462   0.03507  -0.0134   0.8304   0.8086
   2.000   0.0759   0.04499   0.03542  -0.0168   0.8195   0.8151
   2.250   0.0995   0.04540   0.03582  -0.0183   0.8077   0.8215
   2.500   0.1205   0.04584   0.03628  -0.0188   0.7964   0.8281
   2.750   0.1578   0.04638   0.03680  -0.0220   0.7854   0.8358
   3.000   0.1824   0.04679   0.03726  -0.0227   0.7743   0.8429
   3.250   0.2029   0.04752   0.03801  -0.0238   0.7627   0.8512
   3.500   0.2300   0.04803   0.03857  -0.0247   0.7522   0.8599
   3.750   0.2604   0.04857   0.03916  -0.0264   0.7412   0.8697
   4.000   0.2730   0.04945   0.04009  -0.0262   0.7297   0.8797
   4.250   0.2978   0.05010   0.04082  -0.0269   0.7189   0.8913
   4.500   0.3314   0.05053   0.04135  -0.0284   0.7082   0.9057
   4.750   0.3417   0.05165   0.04256  -0.0283   0.6962   0.9207
   5.000   0.3683   0.05261   0.04366  -0.0301   0.6842   0.9405
   5.500   0.4674   0.05408   0.04537  -0.0399   0.6586   1.0000
   5.750   0.4887   0.05583   0.04719  -0.0428   0.6447   1.0000
   6.000   0.5139   0.05763   0.04905  -0.0460   0.6308   1.0000
   6.250   0.5443   0.05927   0.05075  -0.0493   0.6167   1.0000
   6.500   0.5762   0.06089   0.05244  -0.0524   0.6027   1.0000
   6.750   0.6102   0.06230   0.05392  -0.0553   0.5883   1.0000
   7.000   0.6448   0.06356   0.05524  -0.0578   0.5738   1.0000
   7.250   0.6807   0.06454   0.05631  -0.0597   0.5593   1.0000
   7.500   0.7198   0.06502   0.05688  -0.0611   0.5447   1.0000
   7.750   0.7609   0.06503   0.05701  -0.0620   0.5302   1.0000
   8.000   0.7803   0.06652   0.05856  -0.0621   0.5146   1.0000
   8.250   0.7935   0.06853   0.06063  -0.0620   0.4992   1.0000
   8.500   0.8123   0.06991   0.06211  -0.0617   0.4836   1.0000
   8.750   0.8258   0.07180   0.06409  -0.0613   0.4681   1.0000
   9.000   0.8436   0.07317   0.06555  -0.0607   0.4523   1.0000
   9.250   0.8542   0.07532   0.06778  -0.0602   0.4369   1.0000
   9.500   1.1618   0.04705   0.04016  -0.0617   0.4038   1.0000
   9.750   1.0821   0.05495   0.04812  -0.0548   0.3977   1.0000
  10.000   0.8784   0.08270   0.07541  -0.0588   0.3910   1.0000
  10.250   1.2398   0.04654   0.03968  -0.0572   0.3338   1.0000
  10.500   1.2779   0.04592   0.03887  -0.0568   0.3066   1.0000
  10.750   1.2801   0.04746   0.04048  -0.0537   0.2884   1.0000
  11.000   1.2853   0.04891   0.04195  -0.0509   0.2706   1.0000
  11.250   1.2944   0.05022   0.04322  -0.0485   0.2525   1.0000
  11.500   1.3222   0.05106   0.04379  -0.0479   0.2306   1.0000
  11.750   1.3051   0.05383   0.04683  -0.0437   0.2217   1.0000
  12.000   1.3309   0.05513   0.04791  -0.0431   0.2025   1.0000
  12.250   1.0737   0.08286   0.07672  -0.0430   0.2525   1.0000
  12.500   1.0307   0.09402   0.08786  -0.0469   0.2481   1.0000
  12.750   1.1123   0.08358   0.07761  -0.0397   0.2228   1.0000
  13.000   1.1379   0.08329   0.07736  -0.0377   0.2073   1.0000
  13.250   1.1331   0.08753   0.08164  -0.0379   0.1989   1.0000
  13.500   0.8582   0.14723   0.14067  -0.0734   0.2488   1.0000
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