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EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 558 AIRFOIL (e558-il)
Reynolds number: 200,000
Max Cl/Cd: 67.65 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e558-il-200000.txt
Download as CSV file: xf-e558-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.5513   0.11030   0.10624  -0.0490   1.0000   0.0297
 -14.500  -0.5824   0.10001   0.09586  -0.0543   1.0000   0.0291
 -14.250  -0.6256   0.08809   0.08375  -0.0617   1.0000   0.0288
 -14.000  -0.6507   0.08049   0.07601  -0.0663   1.0000   0.0282
 -13.750  -0.6785   0.07309   0.06845  -0.0708   1.0000   0.0280
 -13.500  -0.7017   0.06683   0.06201  -0.0746   1.0000   0.0279
 -13.250  -0.7207   0.06149   0.05649  -0.0775   1.0000   0.0276
 -13.000  -0.7361   0.05689   0.05173  -0.0797   1.0000   0.0276
 -12.750  -0.7480   0.05298   0.04767  -0.0813   1.0000   0.0276
 -12.500  -0.7580   0.04954   0.04410  -0.0824   1.0000   0.0278
 -12.250  -0.7666   0.04651   0.04094  -0.0828   1.0000   0.0279
 -12.000  -0.7753   0.04385   0.03816  -0.0828   1.0000   0.0282
 -11.750  -0.7871   0.04144   0.03562  -0.0820   1.0000   0.0286
 -11.500  -0.8010   0.03955   0.03363  -0.0798   1.0000   0.0287
 -11.250  -0.8105   0.03775   0.03170  -0.0776   1.0000   0.0290
 -11.000  -0.8123   0.03610   0.02991  -0.0755   1.0000   0.0293
 -10.750  -0.8123   0.03464   0.02826  -0.0733   1.0000   0.0297
 -10.500  -0.8058   0.03297   0.02666  -0.0711   1.0000   0.0304
 -10.250  -0.7998   0.03171   0.02542  -0.0690   1.0000   0.0309
 -10.000  -0.7936   0.03053   0.02424  -0.0669   1.0000   0.0316
  -9.750  -0.7867   0.02941   0.02306  -0.0649   1.0000   0.0325
  -9.500  -0.7787   0.02834   0.02193  -0.0630   1.0000   0.0333
  -9.250  -0.7556   0.02716   0.02060  -0.0637   0.9977   0.0347
  -9.000  -0.7184   0.02545   0.01898  -0.0676   0.9924   0.0369
  -8.750  -0.6796   0.02414   0.01756  -0.0711   0.9860   0.0405
  -8.500  -0.6421   0.02260   0.01603  -0.0748   0.9798   0.0464
  -8.250  -0.6050   0.02077   0.01427  -0.0786   0.9732   0.0584
  -8.000  -0.5704   0.01895   0.01260  -0.0816   0.9656   0.0875
  -7.750  -0.5302   0.01783   0.01159  -0.0851   0.9599   0.1236
  -7.500  -0.4946   0.01716   0.01096  -0.0872   0.9513   0.1507
  -7.250  -0.4521   0.01664   0.01046  -0.0904   0.9461   0.1761
  -7.000  -0.4167   0.01628   0.01007  -0.0921   0.9370   0.1979
  -6.750  -0.3737   0.01600   0.00980  -0.0951   0.9319   0.2199
  -6.500  -0.3373   0.01576   0.00951  -0.0966   0.9232   0.2371
  -6.250  -0.2953   0.01546   0.00916  -0.0992   0.9174   0.2529
  -6.000  -0.2539   0.01518   0.00883  -0.1016   0.9103   0.2672
  -5.750  -0.2128   0.01489   0.00845  -0.1040   0.9016   0.2805
  -5.500  -0.1716   0.01468   0.00814  -0.1064   0.8920   0.2931
  -5.250  -0.1290   0.01439   0.00786  -0.1090   0.8819   0.3041
  -5.000  -0.0924   0.01418   0.00753  -0.1105   0.8677   0.3148
  -4.750  -0.0566   0.01406   0.00733  -0.1118   0.8530   0.3249
  -4.500  -0.0229   0.01391   0.00710  -0.1127   0.8377   0.3341
  -4.250   0.0088   0.01386   0.00692  -0.1132   0.8220   0.3438
  -4.000   0.0389   0.01376   0.00673  -0.1134   0.8065   0.3520
  -3.750   0.0684   0.01375   0.00658  -0.1134   0.7915   0.3611
  -3.500   0.0954   0.01368   0.00643  -0.1130   0.7757   0.3690
  -3.250   0.1225   0.01367   0.00635  -0.1126   0.7605   0.3775
  -3.000   0.1497   0.01362   0.00619  -0.1123   0.7462   0.3856
  -2.750   0.1771   0.01362   0.00612  -0.1119   0.7327   0.3938
  -2.500   0.2049   0.01361   0.00595  -0.1117   0.7198   0.4024
  -2.250   0.2309   0.01357   0.00591  -0.1112   0.7060   0.4100
  -2.000   0.2580   0.01360   0.00581  -0.1109   0.6932   0.4192
  -1.750   0.2850   0.01356   0.00575  -0.1105   0.6815   0.4267
  -1.500   0.3118   0.01359   0.00567  -0.1101   0.6690   0.4361
  -1.250   0.3382   0.01356   0.00565  -0.1097   0.6572   0.4441
  -1.000   0.3658   0.01362   0.00558  -0.1095   0.6468   0.4536
  -0.750   0.3918   0.01358   0.00556  -0.1090   0.6350   0.4618
  -0.500   0.4188   0.01365   0.00555  -0.1087   0.6244   0.4720
  -0.250   0.4457   0.01365   0.00553  -0.1083   0.6143   0.4808
   0.000   0.4723   0.01371   0.00555  -0.1080   0.6039   0.4914
   0.250   0.4996   0.01376   0.00556  -0.1077   0.5949   0.5010
   0.500   0.5257   0.01379   0.00560  -0.1073   0.5844   0.5122
   0.750   0.5531   0.01387   0.00564  -0.1071   0.5761   0.5229
   1.000   0.5789   0.01389   0.00572  -0.1066   0.5664   0.5344
   1.250   0.6067   0.01402   0.00576  -0.1065   0.5586   0.5477
   1.500   0.6320   0.01403   0.00588  -0.1059   0.5491   0.5600
   1.750   0.6595   0.01414   0.00595  -0.1057   0.5417   0.5742
   2.000   0.6849   0.01418   0.00610  -0.1052   0.5332   0.5896
   2.250   0.7118   0.01427   0.00619  -0.1049   0.5259   0.6067
   2.500   0.7375   0.01436   0.00637  -0.1044   0.5181   0.6256
   2.750   0.7633   0.01442   0.00650  -0.1039   0.5106   0.6475
   3.000   0.7896   0.01455   0.00668  -0.1035   0.5041   0.6739
   3.250   0.8138   0.01458   0.00689  -0.1026   0.4968   0.7040
   3.500   0.8386   0.01465   0.00705  -0.1018   0.4906   0.7432
   3.750   0.8597   0.01468   0.00728  -0.1002   0.4840   0.7942
   4.000   0.8784   0.01460   0.00741  -0.0978   0.4776   0.8729
   4.250   0.9157   0.01471   0.00749  -0.0996   0.4716   1.0000
   4.500   0.9414   0.01494   0.00775  -0.0994   0.4647   1.0000
   4.750   0.9686   0.01518   0.00794  -0.0993   0.4584   1.0000
   5.000   0.9968   0.01553   0.00819  -0.0995   0.4529   1.0000
   5.250   1.0216   0.01578   0.00850  -0.0990   0.4465   1.0000
   5.500   1.0483   0.01604   0.00872  -0.0989   0.4406   1.0000
   5.750   1.0755   0.01640   0.00903  -0.0988   0.4352   1.0000
   6.000   1.0995   0.01667   0.00937  -0.0982   0.4288   1.0000
   6.250   1.1259   0.01695   0.00962  -0.0980   0.4232   1.0000
   6.500   1.1523   0.01733   0.00997  -0.0978   0.4178   1.0000
   6.750   1.1756   0.01761   0.01034  -0.0970   0.4116   1.0000
   7.000   1.2014   0.01790   0.01061  -0.0967   0.4060   1.0000
   7.250   1.2273   0.01830   0.01100  -0.0964   0.4007   1.0000
   7.500   1.2493   0.01859   0.01140  -0.0955   0.3944   1.0000
   7.750   1.2746   0.01889   0.01168  -0.0950   0.3888   1.0000
   8.000   1.2990   0.01929   0.01210  -0.0945   0.3831   1.0000
   8.250   1.3200   0.01959   0.01250  -0.0934   0.3766   1.0000
   8.500   1.3449   0.01988   0.01276  -0.0929   0.3708   1.0000
   8.750   1.3659   0.02027   0.01324  -0.0918   0.3645   1.0000
   9.000   1.3866   0.02055   0.01359  -0.0907   0.3579   1.0000
   9.250   1.4126   0.02094   0.01389  -0.0905   0.3519   1.0000
   9.500   1.4277   0.02126   0.01441  -0.0883   0.3451   1.0000
   9.750   1.4481   0.02153   0.01470  -0.0871   0.3385   1.0000
  10.000   1.4666   0.02193   0.01516  -0.0857   0.3318   1.0000
  10.250   1.4820   0.02222   0.01555  -0.0837   0.3243   1.0000
  10.500   1.5000   0.02258   0.01589  -0.0821   0.3172   1.0000
  10.750   1.5101   0.02292   0.01638  -0.0793   0.3094   1.0000
  11.000   1.5260   0.02330   0.01670  -0.0774   0.3024   1.0000
  11.250   1.5309   0.02375   0.01735  -0.0738   0.2949   1.0000
  11.500   1.5424   0.02421   0.01777  -0.0714   0.2876   1.0000
  11.750   1.5472   0.02482   0.01855  -0.0681   0.2795   1.0000
  12.000   1.5547   0.02544   0.01912  -0.0654   0.2712   1.0000
  12.250   1.5569   0.02625   0.02011  -0.0622   0.2620   1.0000
  12.500   1.5600   0.02718   0.02104  -0.0594   0.2528   1.0000
  12.750   1.5603   0.02832   0.02226  -0.0567   0.2423   1.0000
  13.000   1.5606   0.02967   0.02369  -0.0542   0.2315   1.0000
  13.250   1.5591   0.03129   0.02533  -0.0520   0.2209   1.0000
  13.500   1.5557   0.03322   0.02726  -0.0500   0.2103   1.0000
  13.750   1.5535   0.03529   0.02943  -0.0484   0.1992   1.0000
  14.000   1.5492   0.03771   0.03188  -0.0471   0.1889   1.0000
  14.250   1.5416   0.04056   0.03473  -0.0459   0.1791   1.0000
  14.500   1.5349   0.04356   0.03778  -0.0451   0.1691   1.0000
  14.750   1.5269   0.04686   0.04113  -0.0446   0.1595   1.0000
  15.000   1.5152   0.05069   0.04496  -0.0444   0.1510   1.0000
  15.250   1.5060   0.05451   0.04885  -0.0445   0.1419   1.0000
  15.500   1.4953   0.05863   0.05302  -0.0448   0.1341   1.0000
  15.750   1.4826   0.06316   0.05756  -0.0454   0.1265   1.0000
  16.000   1.4725   0.06757   0.06204  -0.0462   0.1190   1.0000
  16.250   1.4585   0.07258   0.06705  -0.0472   0.1126   1.0000
  16.500   1.4492   0.07719   0.07175  -0.0484   0.1055   1.0000
  16.750   1.4354   0.08245   0.07699  -0.0498   0.0999   1.0000
  17.000   1.4268   0.08719   0.08184  -0.0512   0.0934   1.0000
  17.250   1.4138   0.09256   0.08718  -0.0529   0.0881   1.0000
  17.500   1.4054   0.09749   0.09222  -0.0546   0.0821   1.0000
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