Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 500,000
Max Cl/Cd: 100.53 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e639-il-500000.txt
Download as CSV file: xf-e639-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2723   0.10330   0.10120  -0.0265   1.0000   0.0157
  -9.500  -0.2694   0.10010   0.09803  -0.0276   1.0000   0.0160
  -9.250  -0.2740   0.09605   0.09402  -0.0314   1.0000   0.0166
  -9.000  -0.2441   0.08940   0.08734  -0.0426   0.9368   0.0167
  -8.750  -0.1880   0.07953   0.07715  -0.0620   0.8610   0.0170
  -8.500  -0.1823   0.07737   0.07466  -0.0615   0.7937   0.0172
  -8.250  -0.1801   0.07513   0.07227  -0.0613   0.7591   0.0174
  -8.000  -0.1819   0.07230   0.06935  -0.0622   0.7339   0.0175
  -7.750  -0.1822   0.07011   0.06708  -0.0625   0.7130   0.0180
  -7.500  -0.1898   0.06703   0.06393  -0.0633   0.6964   0.0180
  -7.250  -0.1878   0.06412   0.06093  -0.0644   0.6808   0.0182
  -6.750  -0.1794   0.05767   0.05429  -0.0663   0.6543   0.0192
  -6.500  -0.1721   0.05415   0.05063  -0.0670   0.6428   0.0199
  -6.250  -0.1497   0.03575   0.03207  -0.0631   0.6156   0.0212
  -6.000  -0.1550   0.04422   0.04010  -0.0670   0.6245   0.0214
  -5.750  -0.1434   0.04178   0.03759  -0.0664   0.6137   0.0217
  -5.500  -0.1289   0.03994   0.03563  -0.0657   0.6033   0.0221
  -5.250  -0.1127   0.03811   0.03369  -0.0650   0.5928   0.0228
  -5.000  -0.0954   0.03598   0.03138  -0.0641   0.5833   0.0238
  -4.750  -0.0718   0.03392   0.02878  -0.0618   0.5749   0.0266
  -4.500  -0.0606   0.02970   0.02438  -0.0605   0.5668   0.0274
  -4.250  -0.0410   0.02839   0.02298  -0.0599   0.5578   0.0282
  -4.000  -0.0198   0.02718   0.02165  -0.0591   0.5487   0.0295
  -3.750   0.0075   0.02740   0.02141  -0.0573   0.5407   0.0334
  -3.500   0.0230   0.02350   0.01736  -0.0562   0.5337   0.0350
  -3.250   0.0457   0.02247   0.01622  -0.0556   0.5262   0.0365
  -3.000   0.0707   0.02174   0.01530  -0.0547   0.5185   0.0400
  -2.750   0.0928   0.02011   0.01338  -0.0536   0.5118   0.0443
  -2.500   0.1176   0.01926   0.01247  -0.0531   0.5045   0.0470
  -2.250   0.1423   0.01868   0.01154  -0.0520   0.4983   0.0543
  -2.000   0.1710   0.01546   0.00793  -0.0504   0.4930   0.0356
  -1.750   0.1986   0.01405   0.00634  -0.0495   0.4870   0.0298
  -1.500   0.2247   0.01312   0.00521  -0.0487   0.4815   0.0281
  -1.250   0.2505   0.01257   0.00462  -0.0480   0.4757   0.0280
  -1.000   0.2754   0.01216   0.00416  -0.0473   0.4701   0.0286
  -0.750   0.3005   0.01187   0.00382  -0.0466   0.4651   0.0293
  -0.500   0.3261   0.01161   0.00355  -0.0460   0.4601   0.0305
  -0.250   0.3517   0.01145   0.00333  -0.0455   0.4553   0.0321
   0.000   0.3773   0.01133   0.00315  -0.0449   0.4507   0.0332
   0.250   0.4031   0.01111   0.00291  -0.0444   0.4461   0.0355
   0.500   0.4293   0.01103   0.00279  -0.0439   0.4415   0.0402
   0.750   0.4536   0.01079   0.00274  -0.0432   0.4375   0.1191
   1.000   0.5187   0.00899   0.00332  -0.0505   0.4323   0.9754
   1.250   0.6145   0.00930   0.00344  -0.0646   0.4257   0.9943
   1.500   0.6694   0.00934   0.00334  -0.0705   0.4208   1.0000
   1.750   0.6927   0.00937   0.00335  -0.0697   0.4173   1.0000
   2.000   0.7158   0.00942   0.00338  -0.0689   0.4139   1.0000
   2.250   0.7388   0.00950   0.00340  -0.0680   0.4105   1.0000
   2.500   0.7615   0.00965   0.00346  -0.0671   0.4069   1.0000
   2.750   0.7848   0.00970   0.00352  -0.0663   0.4038   1.0000
   3.000   0.8080   0.00977   0.00358  -0.0655   0.4006   1.0000
   3.250   0.8310   0.00985   0.00365  -0.0646   0.3975   1.0000
   3.500   0.8538   0.00998   0.00372  -0.0637   0.3944   1.0000
   3.750   0.8765   0.01016   0.00386  -0.0628   0.3912   1.0000
   4.000   0.8994   0.01023   0.00396  -0.0619   0.3882   1.0000
   4.250   0.9223   0.01034   0.00407  -0.0610   0.3852   1.0000
   4.500   0.9451   0.01045   0.00418  -0.0601   0.3823   1.0000
   4.750   0.9677   0.01061   0.00432  -0.0592   0.3794   1.0000
   5.000   0.9902   0.01082   0.00449  -0.0583   0.3761   1.0000
   5.250   1.0129   0.01092   0.00464  -0.0574   0.3734   1.0000
   5.500   1.0356   0.01105   0.00480  -0.0565   0.3705   1.0000
   5.750   1.0582   0.01119   0.00495  -0.0556   0.3676   1.0000
   6.000   1.0806   0.01137   0.00511  -0.0547   0.3646   1.0000
   6.250   1.1031   0.01162   0.00534  -0.0538   0.3615   1.0000
   6.500   1.1255   0.01173   0.00553  -0.0529   0.3587   1.0000
   6.750   1.1478   0.01186   0.00571  -0.0520   0.3554   1.0000
   7.000   1.1700   0.01201   0.00587  -0.0510   0.3521   1.0000
   7.250   1.1921   0.01223   0.00607  -0.0501   0.3487   1.0000
   7.500   1.2141   0.01242   0.00632  -0.0492   0.3454   1.0000
   7.750   1.2359   0.01254   0.00651  -0.0482   0.3417   1.0000
   8.000   1.2576   0.01268   0.00668  -0.0472   0.3378   1.0000
   8.250   1.2790   0.01291   0.00690  -0.0462   0.3340   1.0000
   8.500   1.3005   0.01309   0.00715  -0.0452   0.3303   1.0000
   8.750   1.3219   0.01323   0.00737  -0.0442   0.3263   1.0000
   9.000   1.3430   0.01340   0.00758  -0.0431   0.3223   1.0000
   9.250   1.3635   0.01370   0.00786  -0.0421   0.3181   1.0000
   9.500   1.3843   0.01381   0.00810  -0.0410   0.3137   1.0000
   9.750   1.4044   0.01397   0.00831  -0.0398   0.3084   1.0000
  10.000   1.4234   0.01425   0.00859  -0.0385   0.3035   1.0000
  10.250   1.4440   0.01440   0.00888  -0.0374   0.2985   1.0000
  10.500   1.4628   0.01463   0.00915  -0.0361   0.2927   1.0000
  10.750   1.4811   0.01489   0.00946  -0.0347   0.2864   1.0000
  11.000   1.4973   0.01516   0.00975  -0.0330   0.2771   1.0000
  11.250   1.5139   0.01545   0.01011  -0.0315   0.2670   1.0000
  11.500   1.5262   0.01583   0.01051  -0.0291   0.2565   1.0000
  11.750   1.5352   0.01631   0.01098  -0.0263   0.2460   1.0000
  12.000   1.5428   0.01690   0.01157  -0.0235   0.2340   1.0000
  12.250   1.5491   0.01763   0.01228  -0.0206   0.2203   1.0000
  12.500   1.5537   0.01850   0.01316  -0.0179   0.2068   1.0000
  12.750   1.5542   0.01967   0.01430  -0.0149   0.1911   1.0000
  13.000   1.5528   0.02110   0.01572  -0.0123   0.1773   1.0000
  13.250   1.5473   0.02302   0.01760  -0.0099   0.1624   1.0000
  13.500   1.5409   0.02528   0.01986  -0.0081   0.1501   1.0000
  13.750   1.5325   0.02802   0.02260  -0.0068   0.1385   1.0000
  14.000   1.5226   0.03113   0.02573  -0.0060   0.1281   1.0000
  14.250   1.5126   0.03448   0.02910  -0.0055   0.1182   1.0000
  14.500   1.4990   0.03833   0.03297  -0.0053   0.1089   1.0000
  15.000   1.4753   0.04600   0.04075  -0.0053   0.0965   1.0000
  15.250   1.4592   0.05042   0.04521  -0.0056   0.0909   1.0000
  15.500   1.4460   0.05465   0.04949  -0.0060   0.0844   1.0000
  15.750   1.4288   0.05951   0.05438  -0.0067   0.0787   1.0000
  16.000   1.4196   0.06352   0.05846  -0.0073   0.0742   1.0000
  16.250   1.4056   0.06823   0.06322  -0.0082   0.0693   1.0000
  16.500   1.3935   0.07277   0.06780  -0.0092   0.0637   1.0000
  16.750   1.3802   0.07758   0.07264  -0.0103   0.0589   1.0000
  17.000   1.3693   0.08218   0.07728  -0.0114   0.0537   1.0000
  17.250   1.3562   0.08712   0.08225  -0.0128   0.0488   1.0000
  17.500   1.3466   0.09168   0.08685  -0.0140   0.0440   1.0000
  17.750   1.3352   0.09658   0.09177  -0.0155   0.0392   1.0000
  18.000   1.3231   0.10167   0.09686  -0.0171   0.0328   1.0000
  18.250   1.3124   0.10662   0.10184  -0.0188   0.0279   1.0000
<< Back to EPPLER 639 AIRFOIL (e639-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 639 AIRFOIL (e639-il)