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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 200,000
Max Cl/Cd: 95.01 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e376-il-200000-n5.txt
Download as CSV file: xf-e376-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.4264   0.16434   0.16074   0.0170   1.0000   0.0051
 -13.500  -0.4177   0.16139   0.15780   0.0154   1.0000   0.0051
 -13.250  -0.4092   0.15843   0.15485   0.0140   1.0000   0.0052
 -13.000  -0.4004   0.15547   0.15190   0.0125   1.0000   0.0053
 -12.750  -0.3918   0.15254   0.14899   0.0110   1.0000   0.0054
 -12.500  -0.3833   0.14962   0.14608   0.0096   1.0000   0.0055
 -12.250  -0.3744   0.14676   0.14323   0.0082   1.0000   0.0055
 -12.000  -0.3657   0.14388   0.14037   0.0068   1.0000   0.0056
 -11.750  -0.3570   0.14105   0.13756   0.0054   1.0000   0.0057
 -11.500  -0.3482   0.13814   0.13467   0.0040   1.0000   0.0059
 -11.250  -0.3394   0.13531   0.13182   0.0027   1.0000   0.0060
 -11.000  -0.3305   0.13254   0.12908   0.0013   1.0000   0.0061
 -10.750  -0.3216   0.12980   0.12635   0.0000   1.0000   0.0062
 -10.500  -0.3126   0.12704   0.12361  -0.0013   1.0000   0.0064
 -10.250  -0.3033   0.12436   0.12096  -0.0026   1.0000   0.0066
 -10.000  -0.2941   0.12178   0.11841  -0.0039   1.0000   0.0067
  -9.750  -0.2844   0.11932   0.11598  -0.0053   1.0000   0.0069
  -9.250  -0.2653   0.11472   0.11144  -0.0079   1.0000   0.0070
  -7.250  -0.1533   0.09476   0.09134  -0.0287   0.8271   0.0074
  -7.000  -0.1433   0.09057   0.08707  -0.0289   0.8050   0.0076
  -6.750  -0.1317   0.08754   0.08394  -0.0300   0.7838   0.0077
  -6.500  -0.1185   0.08480   0.08112  -0.0315   0.7657   0.0078
  -6.250  -0.1039   0.08231   0.07855  -0.0334   0.7489   0.0079
  -6.000  -0.0878   0.07982   0.07599  -0.0355   0.7341   0.0081
  -5.750  -0.0706   0.07731   0.07341  -0.0379   0.7204   0.0083
  -5.500  -0.0520   0.07487   0.07089  -0.0404   0.7078   0.0086
  -5.250  -0.0319   0.07239   0.06834  -0.0431   0.6958   0.0088
  -5.000  -0.0105   0.06990   0.06577  -0.0460   0.6856   0.0092
  -4.750   0.0124   0.06738   0.06319  -0.0491   0.6755   0.0096
  -4.500   0.0370   0.06490   0.06061  -0.0524   0.6662   0.0103
  -4.250   0.0698   0.06330   0.05889  -0.0569   0.6572   0.0118
  -4.000   0.1099   0.06248   0.05796  -0.0630   0.6482   0.0122
  -3.750   0.1429   0.06051   0.05587  -0.0674   0.6407   0.0123
  -3.500   0.1749   0.05830   0.05356  -0.0714   0.6330   0.0123
  -3.250   0.2058   0.05600   0.05115  -0.0748   0.6260   0.0124
  -3.000   0.2372   0.05365   0.04871  -0.0782   0.6190   0.0124
  -2.750   0.2687   0.05135   0.04628  -0.0813   0.6130   0.0124
  -2.500   0.2929   0.04714   0.04206  -0.0836   0.6066   0.0127
  -2.250   0.3154   0.04373   0.03855  -0.0852   0.6012   0.0132
  -2.000   0.3445   0.04130   0.03606  -0.0878   0.5950   0.0138
  -1.750   0.3763   0.03926   0.03392  -0.0905   0.5893   0.0145
  -1.500   0.4094   0.03738   0.03192  -0.0932   0.5839   0.0157
  -1.250   0.4441   0.03571   0.03014  -0.0959   0.5780   0.0193
  -1.000   0.4849   0.03483   0.02907  -0.0988   0.5730   0.0210
  -0.750   0.5237   0.03386   0.02793  -0.1014   0.5675   0.0212
  -0.500   0.5591   0.03259   0.02651  -0.1034   0.5621   0.0213
  -0.250   0.5923   0.03120   0.02495  -0.1049   0.5576   0.0214
   0.000   0.6167   0.02814   0.02191  -0.1064   0.5525   0.0224
   0.250   0.6467   0.02674   0.02040  -0.1077   0.5476   0.0236
   0.500   0.6784   0.02560   0.01911  -0.1088   0.5432   0.0253
   0.750   0.7125   0.02484   0.01822  -0.1098   0.5379   0.0282
   1.000   0.7480   0.02455   0.01773  -0.1103   0.5333   0.0291
   1.250   0.7791   0.02347   0.01647  -0.1109   0.5293   0.0292
   1.750   0.8390   0.02020   0.01297  -0.1125   0.5196   0.0195
   2.000   0.8688   0.01962   0.01224  -0.1127   0.5157   0.0271
   2.250   0.9003   0.01851   0.01098  -0.1130   0.5108   0.0236
   2.500   0.9319   0.01739   0.00962  -0.1129   0.5062   0.0211
   2.750   0.9612   0.01650   0.00851  -0.1128   0.5023   0.0206
   3.000   0.9908   0.01538   0.00717  -0.1127   0.4978   0.0203
   3.250   1.0190   0.01443   0.00597  -0.1124   0.4931   0.0203
   3.500   1.0461   0.01397   0.00533  -0.1121   0.4888   0.0212
   3.750   1.0728   0.01380   0.00515  -0.1119   0.4842   0.0260
   4.000   1.0999   0.01378   0.00519  -0.1117   0.4790   0.0535
   4.250   1.1262   0.01402   0.00542  -0.1114   0.4744   0.0804
   4.500   1.1527   0.01407   0.00549  -0.1112   0.4691   0.0906
   4.750   1.1792   0.01413   0.00552  -0.1110   0.4634   0.0998
   5.000   1.2055   0.01424   0.00560  -0.1107   0.4578   0.1121
   5.250   1.2318   0.01435   0.00584  -0.1105   0.4505   0.1305
   5.500   1.2578   0.01450   0.00598  -0.1102   0.4444   0.1520
   5.750   1.2840   0.01464   0.00621  -0.1100   0.4370   0.1771
   6.000   1.3098   0.01480   0.00639  -0.1098   0.4300   0.2067
   6.250   1.3333   0.01433   0.00666  -0.1092   0.4213   0.8220
   6.750   1.3883   0.01465   0.00719  -0.1094   0.4034   1.0000
   7.000   1.4136   0.01488   0.00751  -0.1090   0.3928   1.0000
   7.250   1.4384   0.01514   0.00783  -0.1086   0.3813   1.0000
   7.500   1.4630   0.01543   0.00818  -0.1082   0.3683   1.0000
   7.750   1.4871   0.01576   0.00856  -0.1078   0.3529   1.0000
   8.000   1.5103   0.01618   0.00905  -0.1073   0.3290   1.0000
   8.250   1.5293   0.01707   0.00966  -0.1065   0.2719   1.0000
   8.500   1.5453   0.01844   0.01069  -0.1055   0.2127   1.0000
   8.750   1.5577   0.02029   0.01214  -0.1044   0.1515   1.0000
   9.000   1.5691   0.02214   0.01366  -0.1031   0.1031   1.0000
   9.250   1.5782   0.02410   0.01533  -0.1015   0.0606   1.0000
   9.500   1.5859   0.02601   0.01706  -0.0998   0.0318   1.0000
   9.750   1.5892   0.02811   0.01912  -0.0975   0.0121   1.0000
  10.000   1.5946   0.02980   0.02089  -0.0953   0.0084   1.0000
  10.250   1.5971   0.03137   0.02262  -0.0928   0.0076   1.0000
  10.500   1.5976   0.03320   0.02462  -0.0905   0.0071   1.0000
  10.750   1.5976   0.03536   0.02695  -0.0889   0.0068   1.0000
  11.000   1.5969   0.03784   0.02961  -0.0877   0.0065   1.0000
  11.250   1.5950   0.04067   0.03262  -0.0868   0.0062   1.0000
  11.500   1.5926   0.04374   0.03588  -0.0863   0.0061   1.0000
  11.750   1.5889   0.04711   0.03943  -0.0859   0.0059   1.0000
  12.000   1.5841   0.05077   0.04327  -0.0858   0.0058   1.0000
  12.250   1.5782   0.05467   0.04733  -0.0859   0.0057   1.0000
  12.500   1.5707   0.05887   0.05170  -0.0861   0.0056   1.0000
  12.750   1.5616   0.06338   0.05637  -0.0865   0.0054   1.0000
  13.000   1.5517   0.06812   0.06128  -0.0871   0.0052   1.0000
  13.250   1.5402   0.07315   0.06645  -0.0877   0.0050   1.0000
  13.500   1.5358   0.07732   0.07078  -0.0884   0.0049   1.0000
  13.750   1.5317   0.08156   0.07518  -0.0891   0.0046   1.0000
  14.000   1.5265   0.08607   0.07985  -0.0900   0.0045   1.0000
  14.250   1.5210   0.09076   0.08470  -0.0910   0.0044   1.0000
  14.500   1.5154   0.09554   0.08971  -0.0921   0.0043   1.0000
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