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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 500,000
Max Cl/Cd: 118.57 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e379-il-500000-n5.txt
Download as CSV file: xf-e379-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3200   0.11769   0.11514   0.0057   0.8086   0.0023
  -9.000  -0.3121   0.11532   0.11263   0.0050   0.7779   0.0023
  -8.750  -0.3038   0.11289   0.11011   0.0039   0.7531   0.0023
  -8.500  -0.2953   0.11042   0.10757   0.0029   0.7326   0.0023
  -8.250  -0.2868   0.10799   0.10507   0.0019   0.7141   0.0023
  -8.000  -0.2784   0.10568   0.10270   0.0009   0.6983   0.0023
  -7.750  -0.2706   0.10334   0.10031   0.0000   0.6843   0.0023
  -7.500  -0.2612   0.10102   0.09795  -0.0012   0.6717   0.0023
  -7.250  -0.2493   0.09846   0.09535  -0.0032   0.6604   0.0023
  -7.000  -0.2362   0.09585   0.09270  -0.0052   0.6502   0.0023
  -6.750  -0.2222   0.09324   0.09004  -0.0074   0.6395   0.0023
  -6.500  -0.2070   0.09058   0.08735  -0.0098   0.6304   0.0023
  -6.250  -0.1907   0.08787   0.08461  -0.0124   0.6218   0.0023
  -6.000  -0.1734   0.08518   0.08187  -0.0150   0.6143   0.0023
  -5.750  -0.1547   0.08241   0.07907  -0.0179   0.6062   0.0023
  -5.500  -0.1352   0.07970   0.07631  -0.0208   0.5992   0.0023
  -5.250  -0.1140   0.07687   0.07342  -0.0239   0.5925   0.0023
  -5.000  -0.0918   0.07407   0.07057  -0.0271   0.5861   0.0023
  -4.750  -0.0683   0.07127   0.06773  -0.0304   0.5799   0.0023
  -4.500  -0.0436   0.06847   0.06486  -0.0337   0.5741   0.0024
  -4.250  -0.0175   0.06563   0.06198  -0.0372   0.5683   0.0024
  -4.000   0.0097   0.06285   0.05915  -0.0407   0.5629   0.0024
  -3.750   0.0384   0.06005   0.05629  -0.0442   0.5578   0.0024
  -3.500   0.0681   0.05728   0.05347  -0.0478   0.5523   0.0024
  -3.250   0.0955   0.05316   0.04930  -0.0512   0.5476   0.0025
  -3.000   0.1204   0.04967   0.04577  -0.0539   0.5430   0.0027
  -2.750   0.1495   0.04707   0.04311  -0.0569   0.5381   0.0031
  -2.250   0.2143   0.04237   0.03826  -0.0633   0.5286   0.0043
  -2.000   0.2500   0.04042   0.03622  -0.0662   0.5238   0.0065
  -1.750   0.2892   0.03891   0.03459  -0.0692   0.5197   0.0069
  -1.500   0.3289   0.03762   0.03320  -0.0721   0.5150   0.0072
  -1.250   0.3622   0.03552   0.03097  -0.0743   0.5104   0.0072
  -0.750   0.4281   0.03160   0.02684  -0.0779   0.5023   0.0072
  -0.500   0.4607   0.02975   0.02489  -0.0794   0.4979   0.0072
  -0.250   0.4930   0.02801   0.02302  -0.0807   0.4937   0.0073
   1.000   0.6502   0.02000   0.01441  -0.0846   0.4733   0.0073
   1.250   0.6802   0.01802   0.01220  -0.0852   0.4693   0.0066
   1.750   0.7410   0.01548   0.00932  -0.0854   0.4615   0.0056
   2.000   0.7713   0.01423   0.00788  -0.0851   0.4573   0.0053
   2.250   0.8012   0.01288   0.00627  -0.0847   0.4535   0.0050
   2.500   0.8306   0.01133   0.00440  -0.0842   0.4499   0.0048
   2.750   0.8583   0.01026   0.00303  -0.0837   0.4456   0.0049
   3.000   0.8850   0.00976   0.00239  -0.0833   0.4413   0.0054
   3.250   0.9118   0.00973   0.00234  -0.0831   0.4371   0.0066
   3.750   0.9656   0.00979   0.00240  -0.0828   0.4273   0.0216
   4.000   0.9924   0.00981   0.00240  -0.0827   0.4223   0.0212
   4.250   1.0192   0.00984   0.00242  -0.0825   0.4158   0.0209
   4.500   1.0459   0.00991   0.00246  -0.0823   0.4092   0.0208
   4.750   1.0727   0.00998   0.00253  -0.0822   0.4020   0.0210
   5.000   1.0993   0.01009   0.00262  -0.0821   0.3954   0.0220
   5.250   1.1258   0.01013   0.00285  -0.0819   0.3879   0.0936
   5.500   1.1501   0.00970   0.00315  -0.0816   0.3807   0.7060
   6.000   1.2037   0.01199   0.00449  -0.0840   0.1518   1.0000
   6.250   1.2251   0.01323   0.00531  -0.0837   0.0829   1.0000
   6.500   1.2444   0.01489   0.00653  -0.0833   0.0015   1.0000
   6.750   1.2692   0.01525   0.00690  -0.0830   0.0013   1.0000
   7.000   1.2936   0.01567   0.00738  -0.0826   0.0012   1.0000
   7.250   1.3176   0.01612   0.00809  -0.0822   0.0014   1.0000
   7.500   1.3410   0.01670   0.00880  -0.0817   0.0014   1.0000
   7.750   1.3637   0.01739   0.00967  -0.0811   0.0014   1.0000
   8.000   1.3851   0.01825   0.01073  -0.0804   0.0014   1.0000
   8.250   1.4048   0.01934   0.01202  -0.0795   0.0014   1.0000
   8.500   1.4218   0.02073   0.01361  -0.0784   0.0014   1.0000
   8.750   1.4356   0.02237   0.01544  -0.0770   0.0015   1.0000
   9.000   1.4459   0.02423   0.01748  -0.0754   0.0015   1.0000
   9.250   1.4519   0.02629   0.01972  -0.0733   0.0015   1.0000
   9.500   1.4542   0.02843   0.02202  -0.0709   0.0016   1.0000
   9.750   1.4496   0.03065   0.02437  -0.0679   0.0016   1.0000
  10.000   1.4452   0.03332   0.02719  -0.0658   0.0017   1.0000
  10.250   1.4412   0.03648   0.03051  -0.0638   0.0017   1.0000
  12.250   1.4611   0.06003   0.05561  -0.0562   0.0035   1.0000
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