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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 100,000
Max Cl/Cd: 50.58 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e598-il-100000-n5.txt
Download as CSV file: xf-e598-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 598 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3218   0.09487   0.09000  -0.0139   0.7560   0.0237
  -8.250  -0.3189   0.09135   0.08646  -0.0157   0.7445   0.0238
  -8.000  -0.3166   0.08772   0.08281  -0.0176   0.7340   0.0238
  -7.750  -0.3151   0.08392   0.07901  -0.0198   0.7242   0.0236
  -7.500  -0.3153   0.08016   0.07524  -0.0219   0.7159   0.0236
  -7.250  -0.3157   0.07649   0.07158  -0.0246   0.7073   0.0238
  -7.000  -0.3128   0.07218   0.06724  -0.0283   0.7001   0.0239
  -6.750  -0.3078   0.06722   0.06224  -0.0326   0.6929   0.0238
  -6.500  -0.3009   0.06180   0.05672  -0.0370   0.6863   0.0238
  -6.250  -0.2921   0.05567   0.05041  -0.0414   0.6808   0.0238
  -6.000  -0.2822   0.04739   0.04182  -0.0461   0.6751   0.0234
  -5.750  -0.2725   0.03797   0.03169  -0.0493   0.6704   0.0234
  -5.250  -0.2351   0.02834   0.02047  -0.0499   0.6589   0.0254
  -5.000  -0.2110   0.02655   0.01829  -0.0496   0.6525   0.0274
  -4.750  -0.1860   0.02491   0.01618  -0.0491   0.6467   0.0310
  -4.500  -0.1599   0.02383   0.01490  -0.0489   0.6400   0.0344
  -4.250  -0.1339   0.02290   0.01373  -0.0485   0.6344   0.0396
  -4.000  -0.1073   0.02209   0.01273  -0.0481   0.6287   0.0462
  -3.750  -0.0803   0.02144   0.01191  -0.0479   0.6225   0.0550
  -3.500  -0.0536   0.02092   0.01120  -0.0475   0.6174   0.0646
  -3.250  -0.0265   0.02046   0.01064  -0.0472   0.6120   0.0744
  -3.000   0.0007   0.02002   0.01014  -0.0470   0.6063   0.0845
  -2.750   0.0276   0.01961   0.00962  -0.0467   0.6014   0.0949
  -2.500   0.0547   0.01923   0.00914  -0.0463   0.5966   0.1061
  -2.250   0.0821   0.01890   0.00873  -0.0461   0.5910   0.1181
  -2.000   0.1091   0.01861   0.00835  -0.0458   0.5862   0.1310
  -1.500   0.1629   0.01807   0.00779  -0.0452   0.5766   0.1607
  -1.250   0.1899   0.01785   0.00756  -0.0449   0.5716   0.1793
  -1.000   0.2167   0.01762   0.00733  -0.0446   0.5676   0.2017
  -0.750   0.2439   0.01743   0.00720  -0.0444   0.5630   0.2331
  -0.500   0.2714   0.01719   0.00712  -0.0444   0.5577   0.2826
  -0.250   0.2976   0.01670   0.00701  -0.0442   0.5533   0.3947
   0.000   0.3628   0.01519   0.00679  -0.0505   0.5487   1.0000
   0.250   0.3890   0.01539   0.00687  -0.0502   0.5433   1.0000
   0.500   0.4150   0.01556   0.00687  -0.0498   0.5385   1.0000
   0.750   0.4410   0.01572   0.00683  -0.0493   0.5347   1.0000
   1.000   0.4671   0.01592   0.00691  -0.0489   0.5303   1.0000
   1.250   0.4932   0.01615   0.00706  -0.0486   0.5250   1.0000
   1.500   0.5193   0.01633   0.00712  -0.0482   0.5207   1.0000
   1.750   0.5454   0.01650   0.00714  -0.0477   0.5171   1.0000
   2.000   0.5714   0.01678   0.00740  -0.0475   0.5117   1.0000
   2.250   0.5974   0.01701   0.00758  -0.0471   0.5068   1.0000
   2.500   0.6236   0.01719   0.00767  -0.0467   0.5028   1.0000
   2.750   0.6497   0.01742   0.00782  -0.0463   0.4987   1.0000
   3.000   0.6754   0.01773   0.00817  -0.0461   0.4930   1.0000
   3.250   0.7014   0.01795   0.00834  -0.0458   0.4885   1.0000
   3.500   0.7278   0.01812   0.00842  -0.0453   0.4849   1.0000
   3.750   0.7531   0.01848   0.00884  -0.0451   0.4792   1.0000
   4.000   0.7788   0.01875   0.00914  -0.0448   0.4741   1.0000
   4.250   0.8050   0.01893   0.00926  -0.0444   0.4701   1.0000
   4.500   0.8304   0.01925   0.00962  -0.0441   0.4650   1.0000
   4.750   0.8555   0.01959   0.01001  -0.0438   0.4593   1.0000
   5.000   0.8815   0.01978   0.01021  -0.0435   0.4549   1.0000
   5.250   0.9069   0.02006   0.01052  -0.0431   0.4501   1.0000
   5.500   0.9314   0.02046   0.01101  -0.0428   0.4440   1.0000
   5.750   0.9571   0.02065   0.01123  -0.0424   0.4393   1.0000
   6.000   0.9821   0.02096   0.01158  -0.0421   0.4342   1.0000
   6.250   1.0060   0.02136   0.01211  -0.0417   0.4279   1.0000
   6.500   1.0318   0.02152   0.01228  -0.0413   0.4231   1.0000
   6.750   1.0554   0.02195   0.01283  -0.0409   0.4170   1.0000
   7.000   1.0794   0.02228   0.01325  -0.0404   0.4107   1.0000
   7.250   1.1055   0.02238   0.01335  -0.0400   0.4062   1.0000
   7.500   1.1268   0.02298   0.01415  -0.0395   0.3983   1.0000
   7.750   1.1517   0.02314   0.01436  -0.0390   0.3926   1.0000
   8.000   1.1734   0.02363   0.01500  -0.0385   0.3852   1.0000
   8.250   1.1969   0.02388   0.01533  -0.0379   0.3783   1.0000
   8.500   1.2184   0.02431   0.01590  -0.0372   0.3707   1.0000
   8.750   1.2408   0.02460   0.01627  -0.0366   0.3629   1.0000
   9.000   1.2608   0.02511   0.01693  -0.0358   0.3544   1.0000
   9.250   1.2827   0.02536   0.01723  -0.0350   0.3465   1.0000
   9.500   1.2999   0.02603   0.01809  -0.0341   0.3368   1.0000
   9.750   1.3193   0.02644   0.01857  -0.0332   0.3280   1.0000
  10.000   1.3354   0.02706   0.01932  -0.0321   0.3181   1.0000
  10.250   1.3493   0.02783   0.02022  -0.0309   0.3078   1.0000
  10.500   1.3630   0.02851   0.02098  -0.0295   0.2979   1.0000
  10.750   1.3730   0.02938   0.02193  -0.0280   0.2873   1.0000
  11.000   1.3762   0.03058   0.02326  -0.0260   0.2768   1.0000
  11.250   1.3773   0.03192   0.02466  -0.0241   0.2671   1.0000
  11.500   1.3775   0.03353   0.02630  -0.0226   0.2571   1.0000
  11.750   1.3735   0.03581   0.02869  -0.0218   0.2467   1.0000
  12.000   1.3705   0.03818   0.03114  -0.0212   0.2365   1.0000
  12.250   1.3673   0.04068   0.03366  -0.0208   0.2263   1.0000
  12.500   1.3614   0.04368   0.03673  -0.0207   0.2157   1.0000
  12.750   1.3549   0.04686   0.03998  -0.0208   0.2055   1.0000
  13.000   1.3490   0.05002   0.04317  -0.0210   0.1956   1.0000
  13.250   1.3425   0.05333   0.04648  -0.0212   0.1857   1.0000
  13.500   1.3343   0.05703   0.05027  -0.0217   0.1761   1.0000
  13.750   1.3268   0.06066   0.05393  -0.0222   0.1669   1.0000
  14.000   1.3195   0.06432   0.05758  -0.0228   0.1581   1.0000
  14.250   1.3117   0.06836   0.06170  -0.0237   0.1493   1.0000
  14.500   1.3051   0.07226   0.06564  -0.0246   0.1411   1.0000
  14.750   1.2981   0.07639   0.06980  -0.0257   0.1331   1.0000
  15.000   1.2918   0.08057   0.07405  -0.0269   0.1255   1.0000
  15.250   1.2857   0.08471   0.07816  -0.0281   0.1185   1.0000
  15.500   1.2795   0.08913   0.08270  -0.0295   0.1115   1.0000
  15.750   1.2740   0.09332   0.08686  -0.0308   0.1054   1.0000
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