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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=0


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.65 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e379-il-1000000.txt
Download as CSV file: xf-e379-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4024   0.13806   0.13653   0.0199   1.0000   0.0022
 -11.000  -0.3934   0.13515   0.13363   0.0184   1.0000   0.0022
 -10.750  -0.3842   0.13227   0.13076   0.0170   1.0000   0.0022
 -10.500  -0.3751   0.12943   0.12792   0.0155   1.0000   0.0022
 -10.250  -0.3659   0.12661   0.12511   0.0141   1.0000   0.0022
 -10.000  -0.3567   0.12383   0.12235   0.0126   1.0000   0.0022
  -9.750  -0.3474   0.12108   0.11962   0.0112   1.0000   0.0022
  -9.500  -0.3382   0.11838   0.11691   0.0098   1.0000   0.0022
  -9.250  -0.3289   0.11569   0.11423   0.0085   1.0000   0.0022
  -9.000  -0.3157   0.11273   0.11126   0.0060   0.9604   0.0022
  -8.750  -0.2970   0.10955   0.10776   0.0021   0.8584   0.0022
  -8.500  -0.2906   0.10742   0.10544   0.0018   0.8093   0.0022
  -8.250  -0.2831   0.10519   0.10308   0.0012   0.7760   0.0022
  -2.000   0.2546   0.03844   0.03497  -0.0672   0.5329   0.0030
  -1.750   0.2867   0.03637   0.03286  -0.0697   0.5285   0.0037
  -1.500   0.3205   0.03440   0.03081  -0.0722   0.5238   0.0057
  -1.250   0.3579   0.03349   0.02976  -0.0740   0.5191   0.0070
   0.000   0.5251   0.02506   0.02087  -0.0817   0.4977   0.0072
   0.250   0.5572   0.02352   0.01921  -0.0826   0.4936   0.0073
   0.500   0.5890   0.02197   0.01757  -0.0834   0.4898   0.0073
   2.250   0.8025   0.01130   0.00579  -0.0843   0.4617   0.0077
   2.500   0.8311   0.01003   0.00428  -0.0840   0.4575   0.0064
   2.750   0.8590   0.00886   0.00279  -0.0835   0.4533   0.0059
   3.000   0.8857   0.00809   0.00183  -0.0831   0.4492   0.0059
   3.250   0.9128   0.00793   0.00164  -0.0828   0.4443   0.0069
   3.500   0.9400   0.00810   0.00177  -0.0827   0.4387   0.0139
   3.750   0.9670   0.00810   0.00188  -0.0827   0.4330   0.0300
   4.000   0.9939   0.00812   0.00186  -0.0826   0.4270   0.0283
   4.250   1.0209   0.00809   0.00181  -0.0824   0.4216   0.0274
   4.500   1.0479   0.00811   0.00182  -0.0823   0.4157   0.0264
   4.750   1.0748   0.00818   0.00187  -0.0821   0.4097   0.0257
   5.000   1.1018   0.00824   0.00193  -0.0820   0.4033   0.0256
   5.250   1.1286   0.00832   0.00205  -0.0819   0.3922   0.0504
   5.500   1.1529   0.00888   0.00231  -0.0818   0.3162   0.1557
   5.750   1.1847   0.00882   0.00299  -0.0841   0.2306   1.0000
   6.000   1.2037   0.01084   0.00416  -0.0838   0.0887   1.0000
   6.250   1.2245   0.01233   0.00519  -0.0834   0.0019   1.0000
   6.500   1.2499   0.01261   0.00545  -0.0832   0.0017   1.0000
   6.750   1.2752   0.01292   0.00579  -0.0829   0.0017   1.0000
   7.000   1.3002   0.01330   0.00623  -0.0825   0.0018   1.0000
   7.250   1.3248   0.01374   0.00693  -0.0821   0.0020   1.0000
   7.500   1.3488   0.01431   0.00764  -0.0816   0.0023   1.0000
   7.750   1.3720   0.01499   0.00845  -0.0810   0.0027   1.0000
   8.000   1.3944   0.01583   0.00945  -0.0803   0.0037   1.0000
   9.500   1.4010   0.01394   0.00884  -0.0633   0.0058   1.0000
   9.750   1.4003   0.01548   0.01051  -0.0608   0.0054   1.0000
  10.000   1.3997   0.01755   0.01270  -0.0587   0.0050   1.0000
  10.250   1.4002   0.02007   0.01535  -0.0569   0.0046   1.0000
  10.500   1.4010   0.02284   0.01825  -0.0554   0.0042   1.0000
  10.750   1.4008   0.02600   0.02155  -0.0539   0.0039   1.0000
  11.000   1.3992   0.02947   0.02516  -0.0526   0.0037   1.0000
  11.250   1.3963   0.03340   0.02931  -0.0517   0.0035   1.0000
  11.500   1.3911   0.03770   0.03376  -0.0510   0.0033   1.0000
  11.750   1.3837   0.04248   0.03871  -0.0506   0.0032   1.0000
  12.000   1.3741   0.04776   0.04415  -0.0506   0.0031   1.0000
  12.250   1.3621   0.05339   0.04994  -0.0508   0.0030   1.0000
  12.500   1.3493   0.05942   0.05613  -0.0513   0.0030   1.0000
  12.750   1.3347   0.06578   0.06265  -0.0522   0.0030   1.0000
  13.000   1.3187   0.07229   0.06932  -0.0535   0.0029   1.0000
  13.250   1.3029   0.07895   0.07613  -0.0552   0.0029   1.0000
  13.500   1.2861   0.08576   0.08309  -0.0573   0.0029   1.0000
  13.750   1.2683   0.09261   0.09009  -0.0597   0.0029   1.0000
  14.000   1.2498   0.09961   0.09724  -0.0624   0.0029   1.0000
  14.250   1.2297   0.10651   0.10429  -0.0655   0.0029   1.0000
  14.500   1.2023   0.11302   0.11096  -0.0687   0.0030   1.0000
  14.750   1.1836   0.11911   0.11717  -0.0721   0.0029   1.0000
  15.000   1.1625   0.12625   0.12445  -0.0762   0.0030   1.0000
  15.250   1.1472   0.13270   0.13102  -0.0802   0.0030   1.0000
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