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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 200,000
Max Cl/Cd: 62.73 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e639-il-200000.txt
Download as CSV file: xf-e639-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 639 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1834   0.09107   0.08826  -0.0332   1.0000   0.0356
  -9.000  -0.1815   0.08804   0.08530  -0.0334   1.0000   0.0362
  -8.750  -0.2719   0.09386   0.09083  -0.0349   1.0000   0.0341
  -8.500  -0.2632   0.09097   0.08799  -0.0334   1.0000   0.0348
  -8.250  -0.2608   0.08827   0.08536  -0.0333   1.0000   0.0354
  -8.000  -0.2609   0.08569   0.08288  -0.0334   1.0000   0.0360
  -7.750  -0.2327   0.08035   0.07753  -0.0424   0.9421   0.0377
  -7.500  -0.1924   0.07281   0.06977  -0.0606   0.8814   0.0405
  -7.250  -0.1817   0.06863   0.06516  -0.0701   0.8307   0.0417
  -7.000  -0.1803   0.06621   0.06235  -0.0712   0.7997   0.0420
  -6.750  -0.1729   0.06074   0.05691  -0.0704   0.7773   0.0429
  -6.500  -0.1628   0.05828   0.05436  -0.0691   0.7558   0.0439
  -6.250  -0.1530   0.05593   0.05187  -0.0685   0.7370   0.0452
  -6.000  -0.1425   0.05342   0.04919  -0.0682   0.7210   0.0472
  -5.750  -0.1296   0.05087   0.04639  -0.0683   0.7067   0.0503
  -5.500  -0.1197   0.04801   0.04295  -0.0677   0.6955   0.0534
  -5.250  -0.1059   0.04485   0.03985  -0.0672   0.6825   0.0552
  -5.000  -0.0901   0.04285   0.03776  -0.0664   0.6693   0.0578
  -4.750  -0.0719   0.04096   0.03562  -0.0656   0.6574   0.0622
  -4.500  -0.0560   0.03854   0.03267  -0.0641   0.6478   0.0670
  -4.250  -0.0382   0.03610   0.03021  -0.0635   0.6371   0.0692
  -4.000  -0.0185   0.03441   0.02838  -0.0626   0.6264   0.0733
  -3.750   0.0013   0.03285   0.02630  -0.0611   0.6180   0.0817
  -3.500   0.0216   0.03079   0.02423  -0.0605   0.6083   0.0853
  -3.250   0.0428   0.02963   0.02266  -0.0591   0.5995   0.0971
  -3.000   0.0646   0.02783   0.02083  -0.0585   0.5911   0.1024
  -2.750   0.0861   0.02652   0.01935  -0.0576   0.5824   0.1174
  -2.500   0.1082   0.02539   0.01804  -0.0568   0.5752   0.1353
  -2.000   0.1754   0.02120   0.01232  -0.0525   0.5616   0.0528
  -1.750   0.2022   0.01924   0.01023  -0.0520   0.5548   0.0502
  -1.500   0.2294   0.01820   0.00903  -0.0514   0.5476   0.0492
  -1.250   0.2564   0.01760   0.00826  -0.0508   0.5414   0.0503
  -1.000   0.2830   0.01713   0.00772  -0.0502   0.5346   0.0519
  -0.750   0.3092   0.01658   0.00708  -0.0496   0.5292   0.0524
  -0.500   0.3330   0.01591   0.00644  -0.0487   0.5232   0.0541
  -0.250   0.3570   0.01549   0.00602  -0.0478   0.5173   0.0574
   0.000   0.3823   0.01533   0.00573  -0.0471   0.5125   0.0637
   0.250   0.5386   0.01280   0.00560  -0.0719   0.5013   1.0000
   0.500   0.5621   0.01295   0.00555  -0.0712   0.4970   1.0000
   0.750   0.5846   0.01304   0.00561  -0.0702   0.4915   1.0000
   1.000   0.6076   0.01316   0.00561  -0.0694   0.4866   1.0000
   1.250   0.6312   0.01334   0.00563  -0.0686   0.4828   1.0000
   1.500   0.6537   0.01350   0.00578  -0.0677   0.4782   1.0000
   1.750   0.6765   0.01366   0.00589  -0.0669   0.4736   1.0000
   2.000   0.6999   0.01383   0.00595  -0.0661   0.4696   1.0000
   2.250   0.7233   0.01406   0.00610  -0.0653   0.4659   1.0000
   2.500   0.7453   0.01425   0.00631  -0.0643   0.4613   1.0000
   2.750   0.7683   0.01445   0.00647  -0.0635   0.4574   1.0000
   3.000   0.7920   0.01467   0.00661  -0.0628   0.4540   1.0000
   3.250   0.8152   0.01495   0.00684  -0.0620   0.4504   1.0000
   3.500   0.8368   0.01517   0.00712  -0.0609   0.4461   1.0000
   3.750   0.8596   0.01541   0.00733  -0.0601   0.4423   1.0000
   4.000   0.8834   0.01566   0.00753  -0.0594   0.4391   1.0000
   4.250   0.9073   0.01600   0.00780  -0.0588   0.4361   1.0000
   4.500   0.9280   0.01626   0.00818  -0.0576   0.4319   1.0000
   4.750   0.9503   0.01652   0.00847  -0.0567   0.4280   1.0000
   5.000   0.9739   0.01679   0.00870  -0.0560   0.4248   1.0000
   5.250   0.9989   0.01714   0.00897  -0.0556   0.4220   1.0000
   5.500   1.0190   0.01749   0.00945  -0.0544   0.4182   1.0000
   5.750   1.0402   0.01779   0.00983  -0.0533   0.4141   1.0000
   6.000   1.0633   0.01807   0.01013  -0.0526   0.4108   1.0000
   6.250   1.0881   0.01838   0.01039  -0.0522   0.4080   1.0000
   6.500   1.1096   0.01880   0.01087  -0.0512   0.4045   1.0000
   6.750   1.1293   0.01917   0.01139  -0.0500   0.4004   1.0000
   7.000   1.1515   0.01948   0.01175  -0.0491   0.3968   1.0000
   7.250   1.1762   0.01975   0.01199  -0.0487   0.3937   1.0000
   7.500   1.1991   0.02017   0.01245  -0.0480   0.3903   1.0000
   7.750   1.2168   0.02058   0.01304  -0.0465   0.3858   1.0000
   8.000   1.2385   0.02085   0.01337  -0.0456   0.3818   1.0000
   8.250   1.2640   0.02106   0.01354  -0.0453   0.3783   1.0000
   8.500   1.2840   0.02149   0.01410  -0.0442   0.3743   1.0000
   8.750   1.3018   0.02184   0.01460  -0.0427   0.3694   1.0000
   9.000   1.3251   0.02200   0.01478  -0.0421   0.3652   1.0000
   9.250   1.3509   0.02225   0.01500  -0.0419   0.3612   1.0000
   9.500   1.3644   0.02266   0.01566  -0.0398   0.3558   1.0000
   9.750   1.3860   0.02283   0.01588  -0.0390   0.3512   1.0000
  10.000   1.4139   0.02298   0.01596  -0.0391   0.3471   1.0000
  10.250   1.4242   0.02343   0.01670  -0.0366   0.3413   1.0000
  10.500   1.4453   0.02351   0.01684  -0.0356   0.3360   1.0000
  10.750   1.4660   0.02368   0.01705  -0.0346   0.3307   1.0000
  11.000   1.4783   0.02396   0.01752  -0.0324   0.3243   1.0000
  11.250   1.5018   0.02394   0.01748  -0.0318   0.3188   1.0000
  11.500   1.5099   0.02440   0.01817  -0.0291   0.3125   1.0000
  11.750   1.5261   0.02449   0.01832  -0.0274   0.3062   1.0000
  12.000   1.5356   0.02487   0.01884  -0.0249   0.2996   1.0000
  12.250   1.5434   0.02510   0.01917  -0.0221   0.2925   1.0000
  12.500   1.5463   0.02552   0.01969  -0.0185   0.2856   1.0000
  12.750   1.5475   0.02596   0.02022  -0.0151   0.2777   1.0000
  13.000   1.5452   0.02678   0.02118  -0.0117   0.2692   1.0000
  13.250   1.5449   0.02767   0.02208  -0.0090   0.2601   1.0000
  13.500   1.5391   0.02912   0.02364  -0.0066   0.2498   1.0000
  13.750   1.5331   0.03097   0.02560  -0.0047   0.2392   1.0000
  14.000   1.5250   0.03326   0.02795  -0.0034   0.2280   1.0000
  14.250   1.5153   0.03601   0.03072  -0.0024   0.2171   1.0000
  14.500   1.5027   0.03927   0.03399  -0.0019   0.2059   1.0000
  14.750   1.4891   0.04292   0.03770  -0.0018   0.1950   1.0000
  15.000   1.4744   0.04688   0.04171  -0.0019   0.1846   1.0000
  15.250   1.4576   0.05119   0.04603  -0.0022   0.1746   1.0000
  15.500   1.4394   0.05582   0.05065  -0.0027   0.1651   1.0000
  15.750   1.4239   0.06040   0.05527  -0.0035   0.1563   1.0000
  16.000   1.4075   0.06527   0.06015  -0.0045   0.1471   1.0000
  16.250   1.3918   0.07012   0.06499  -0.0056   0.1392   1.0000
  16.500   1.3779   0.07500   0.06991  -0.0069   0.1308   1.0000
  16.750   1.3644   0.07989   0.07484  -0.0082   0.1230   1.0000
  17.000   1.3508   0.08485   0.07977  -0.0096   0.1157   1.0000
  17.250   1.3393   0.08978   0.08477  -0.0112   0.1081   1.0000
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