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EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 555 AIRFOIL (e555-il)
Reynolds number: 100,000
Max Cl/Cd: 51.16 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e555-il-100000-n5.txt
Download as CSV file: xf-e555-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5663   0.09845   0.09279  -0.0551   1.0000   0.0189
 -13.500  -0.5993   0.08831   0.08245  -0.0608   1.0000   0.0181
 -13.250  -0.6250   0.08075   0.07469  -0.0648   1.0000   0.0180
 -13.000  -0.6433   0.07515   0.06893  -0.0675   1.0000   0.0179
 -12.750  -0.6623   0.06967   0.06323  -0.0696   1.0000   0.0177
 -12.500  -0.6730   0.06577   0.05920  -0.0708   1.0000   0.0180
 -12.250  -0.6838   0.06187   0.05511  -0.0717   1.0000   0.0180
 -12.000  -0.6914   0.05864   0.05174  -0.0721   1.0000   0.0183
 -11.750  -0.6983   0.05560   0.04855  -0.0721   1.0000   0.0188
 -11.500  -0.7029   0.05285   0.04564  -0.0717   1.0000   0.0191
 -11.250  -0.7052   0.05034   0.04296  -0.0709   1.0000   0.0193
 -11.000  -0.7063   0.04800   0.04043  -0.0697   1.0000   0.0198
 -10.750  -0.7047   0.04591   0.03815  -0.0681   1.0000   0.0202
 -10.500  -0.7007   0.04417   0.03632  -0.0663   1.0000   0.0207
 -10.250  -0.6973   0.04270   0.03484  -0.0644   1.0000   0.0210
 -10.000  -0.6959   0.04131   0.03344  -0.0622   1.0000   0.0215
  -9.750  -0.6962   0.04002   0.03211  -0.0597   1.0000   0.0222
  -9.500  -0.6991   0.03883   0.03089  -0.0566   1.0000   0.0228
  -9.250  -0.7063   0.03775   0.02978  -0.0530   1.0000   0.0233
  -9.000  -0.7120   0.03663   0.02860  -0.0497   1.0000   0.0241
  -8.750  -0.7147   0.03546   0.02738  -0.0470   1.0000   0.0251
  -8.500  -0.7081   0.03411   0.02607  -0.0464   0.9983   0.0266
  -8.250  -0.6790   0.03269   0.02453  -0.0488   0.9924   0.0297
  -8.000  -0.6525   0.03104   0.02289  -0.0513   0.9853   0.0326
  -7.750  -0.6264   0.02950   0.02128  -0.0536   0.9776   0.0380
  -7.500  -0.5986   0.02791   0.01965  -0.0562   0.9703   0.0453
  -7.250  -0.5717   0.02631   0.01807  -0.0586   0.9622   0.0568
  -7.000  -0.5450   0.02466   0.01650  -0.0610   0.9543   0.0778
  -6.750  -0.5146   0.02268   0.01476  -0.0645   0.9477   0.1235
  -6.500  -0.4886   0.02009   0.01286  -0.0682   0.9397   0.2358
  -6.250  -0.4547   0.01965   0.01304  -0.0702   0.9337   0.3646
  -6.000  -0.4202   0.01981   0.01304  -0.0716   0.9270   0.4041
  -5.750  -0.3855   0.02003   0.01304  -0.0729   0.9201   0.4303
  -5.500  -0.3464   0.02034   0.01320  -0.0746   0.9159   0.4487
  -5.250  -0.3176   0.02058   0.01329  -0.0746   0.9069   0.4626
  -5.000  -0.2810   0.02109   0.01376  -0.0754   0.9019   0.4762
  -4.750  -0.2503   0.02140   0.01402  -0.0753   0.8942   0.4859
  -4.500  -0.2132   0.02109   0.01347  -0.0774   0.8882   0.4944
  -4.250  -0.1747   0.02084   0.01309  -0.0794   0.8833   0.4985
  -4.000  -0.1447   0.02067   0.01282  -0.0798   0.8744   0.5019
  -3.750  -0.1053   0.02031   0.01229  -0.0822   0.8693   0.5063
  -3.500  -0.0744   0.01991   0.01168  -0.0835   0.8596   0.5117
  -3.250  -0.0370   0.01965   0.01132  -0.0852   0.8535   0.5145
  -3.000  -0.0080   0.01949   0.01109  -0.0854   0.8436   0.5172
  -2.750   0.0292   0.01923   0.01072  -0.0873   0.8369   0.5210
  -2.500   0.0584   0.01901   0.01037  -0.0878   0.8264   0.5252
  -2.250   0.0943   0.01869   0.00991  -0.0897   0.8186   0.5292
  -2.000   0.1237   0.01857   0.00975  -0.0899   0.8085   0.5317
  -1.750   0.1549   0.01845   0.00957  -0.0905   0.7993   0.5349
  -1.500   0.1876   0.01828   0.00933  -0.0914   0.7902   0.5387
  -1.250   0.2173   0.01813   0.00907  -0.0920   0.7797   0.5429
  -1.000   0.2507   0.01796   0.00880  -0.0931   0.7710   0.5463
  -0.750   0.2778   0.01792   0.00876  -0.0930   0.7600   0.5491
  -0.500   0.3069   0.01786   0.00867  -0.0932   0.7499   0.5526
  -0.250   0.3380   0.01777   0.00851  -0.0938   0.7404   0.5568
   0.000   0.3661   0.01771   0.00837  -0.0941   0.7292   0.5612
   0.250   0.3948   0.01767   0.00832  -0.0941   0.7194   0.5640
   0.500   0.4231   0.01765   0.00830  -0.0942   0.7092   0.5673
   0.750   0.4502   0.01766   0.00831  -0.0940   0.6984   0.5714
   1.000   0.4799   0.01764   0.00822  -0.0945   0.6888   0.5762
   1.250   0.5071   0.01765   0.00823  -0.0943   0.6780   0.5799
   1.500   0.5338   0.01769   0.00831  -0.0941   0.6676   0.5833
   1.750   0.5627   0.01771   0.00830  -0.0942   0.6582   0.5875
   2.000   0.5891   0.01777   0.00837  -0.0941   0.6470   0.5925
   2.250   0.6160   0.01783   0.00845  -0.0939   0.6367   0.5967
   2.500   0.6434   0.01789   0.00853  -0.0937   0.6270   0.6010
   2.750   0.6688   0.01799   0.00868  -0.0933   0.6158   0.6059
   3.000   0.6961   0.01808   0.00877  -0.0933   0.6054   0.6112
   3.250   0.7224   0.01817   0.00890  -0.0929   0.5953   0.6153
   3.500   0.7473   0.01830   0.00910  -0.0924   0.5839   0.6206
   3.750   0.7741   0.01843   0.00925  -0.0923   0.5732   0.6270
   4.000   0.7999   0.01854   0.00941  -0.0918   0.5626   0.6318
   4.250   0.8241   0.01869   0.00965  -0.0911   0.5505   0.6375
   4.500   0.8496   0.01886   0.00986  -0.0907   0.5389   0.6440
   4.750   0.8741   0.01901   0.01006  -0.0901   0.5276   0.6497
   5.000   0.8986   0.01918   0.01029  -0.0895   0.5155   0.6570
   5.250   0.9219   0.01938   0.01060  -0.0886   0.5029   0.6637
   5.500   0.9455   0.01958   0.01088  -0.0879   0.4905   0.6713
   5.750   0.9691   0.01980   0.01114  -0.0871   0.4781   0.6789
   6.000   0.9921   0.02002   0.01143  -0.0862   0.4654   0.6871
   6.250   1.0139   0.02027   0.01177  -0.0852   0.4518   0.6959
   6.500   1.0354   0.02054   0.01213  -0.0841   0.4380   0.7060
   6.750   1.0559   0.02081   0.01251  -0.0828   0.4240   0.7158
   7.000   1.0761   0.02111   0.01291  -0.0815   0.4098   0.7271
   7.250   1.0955   0.02143   0.01332  -0.0801   0.3952   0.7395
   7.500   1.1133   0.02176   0.01375  -0.0783   0.3801   0.7528
   8.000   1.1450   0.02249   0.01470  -0.0743   0.3485   0.7864
   8.250   1.1579   0.02288   0.01519  -0.0718   0.3324   0.8083
   8.500   1.1679   0.02326   0.01569  -0.0687   0.3162   0.8382
   9.000   1.1836   0.02409   0.01669  -0.0623   0.2833   1.0000
   9.250   1.1952   0.02491   0.01747  -0.0603   0.2652   1.0000
   9.500   1.2050   0.02583   0.01834  -0.0582   0.2475   1.0000
   9.750   1.2137   0.02685   0.01933  -0.0561   0.2301   1.0000
  10.000   1.2213   0.02797   0.02043  -0.0540   0.2134   1.0000
  10.250   1.2276   0.02921   0.02165  -0.0519   0.1979   1.0000
  10.500   1.2329   0.03059   0.02302  -0.0499   0.1835   1.0000
  10.750   1.2371   0.03210   0.02452  -0.0479   0.1703   1.0000
  11.000   1.2405   0.03375   0.02617  -0.0462   0.1580   1.0000
  11.250   1.2446   0.03546   0.02791  -0.0446   0.1463   1.0000
  11.500   1.2476   0.03732   0.02981  -0.0432   0.1357   1.0000
  11.750   1.2488   0.03941   0.03191  -0.0420   0.1263   1.0000
  12.000   1.2499   0.04161   0.03415  -0.0409   0.1175   1.0000
  12.250   1.2517   0.04387   0.03650  -0.0400   0.1092   1.0000
  12.500   1.2498   0.04653   0.03916  -0.0393   0.1025   1.0000
  12.750   1.2519   0.04897   0.04173  -0.0388   0.0952   1.0000
  13.000   1.2487   0.05198   0.04474  -0.0385   0.0899   1.0000
  13.250   1.2500   0.05469   0.04759  -0.0383   0.0838   1.0000
  13.500   1.2469   0.05792   0.05087  -0.0384   0.0791   1.0000
  13.750   1.2456   0.06109   0.05414  -0.0385   0.0744   1.0000
  14.000   1.2441   0.06441   0.05757  -0.0389   0.0700   1.0000
  14.250   1.2391   0.06821   0.06138  -0.0396   0.0667   1.0000
  14.500   1.2385   0.07165   0.06498  -0.0401   0.0627   1.0000
  14.750   1.2355   0.07548   0.06894  -0.0411   0.0592   1.0000
  15.000   1.2307   0.07961   0.07309  -0.0422   0.0566   1.0000
  15.250   1.2291   0.08346   0.07710  -0.0432   0.0536   1.0000
  15.500   1.2259   0.08763   0.08141  -0.0446   0.0508   1.0000
  15.750   1.2215   0.09206   0.08591  -0.0462   0.0485   1.0000
  16.000   1.2180   0.09635   0.09025  -0.0478   0.0465   1.0000
  16.250   1.2149   0.10083   0.09493  -0.0495   0.0442   1.0000
  16.500   1.2109   0.10547   0.09970  -0.0515   0.0422   1.0000
  16.750   1.2067   0.11017   0.10448  -0.0537   0.0405   1.0000
  17.000   1.2041   0.11453   0.10886  -0.0556   0.0390   1.0000
  17.250   1.1987   0.11978   0.11435  -0.0582   0.0375   1.0000
  17.500   1.1930   0.12511   0.11985  -0.0609   0.0360   1.0000
  17.750   1.1877   0.13038   0.12525  -0.0639   0.0347   1.0000
  18.000   1.1842   0.13528   0.13021  -0.0667   0.0335   1.0000
  18.250   1.1831   0.13960   0.13455  -0.0691   0.0323   1.0000
  18.500   1.1720   0.14658   0.14178  -0.0734   0.0315   1.0000
  18.750   1.1598   0.15397   0.14939  -0.0780   0.0308   1.0000
  19.000   1.1444   0.16237   0.15799  -0.0835   0.0302   1.0000
  19.250   1.1219   0.17308   0.16889  -0.0905   0.0299   1.0000
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