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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 100,000
Max Cl/Cd: 67.36 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e376-il-100000-n5.txt
Download as CSV file: xf-e376-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2569   0.11952   0.11500  -0.0111   1.0000   0.0122
  -8.750  -0.2490   0.11794   0.11349  -0.0125   1.0000   0.0123
  -8.500  -0.2415   0.11644   0.11205  -0.0138   1.0000   0.0123
  -8.250  -0.2313   0.11473   0.11041  -0.0159   1.0000   0.0123
  -8.000  -0.2197   0.11280   0.10854  -0.0182   1.0000   0.0124
  -7.750  -0.2075   0.11090   0.10671  -0.0207   1.0000   0.0124
  -7.500  -0.1949   0.10883   0.10471  -0.0231   1.0000   0.0124
  -7.250  -0.1730   0.10580   0.10175  -0.0278   0.9750   0.0124
  -7.000  -0.1619   0.09633   0.09224  -0.0267   0.9544   0.0128
  -6.750  -0.1393   0.09098   0.08685  -0.0303   0.9262   0.0132
  -6.500  -0.1165   0.08709   0.08290  -0.0342   0.8977   0.0136
  -6.250  -0.0967   0.08408   0.07980  -0.0373   0.8703   0.0139
  -6.000  -0.0790   0.08141   0.07705  -0.0397   0.8454   0.0144
  -5.750  -0.0617   0.07889   0.07444  -0.0418   0.8243   0.0153
  -5.500  -0.0434   0.07651   0.07198  -0.0442   0.8053   0.0162
  -5.250  -0.0237   0.07411   0.06949  -0.0467   0.7885   0.0171
  -5.000  -0.0024   0.07170   0.06699  -0.0495   0.7738   0.0180
  -4.750   0.0204   0.06929   0.06450  -0.0525   0.7602   0.0189
  -4.500   0.0456   0.06699   0.06207  -0.0559   0.7475   0.0199
  -4.250   0.0756   0.06508   0.06006  -0.0601   0.7355   0.0207
  -4.000   0.1089   0.06351   0.05836  -0.0649   0.7245   0.0211
  -3.750   0.1450   0.06212   0.05681  -0.0700   0.7144   0.0213
  -3.500   0.1815   0.06059   0.05514  -0.0750   0.7041   0.0214
  -3.250   0.2015   0.05677   0.05128  -0.0763   0.6958   0.0216
  -3.000   0.2177   0.05287   0.04735  -0.0769   0.6877   0.0224
  -2.750   0.2452   0.05041   0.04479  -0.0796   0.6794   0.0235
  -2.500   0.2760   0.04829   0.04255  -0.0826   0.6718   0.0254
  -2.250   0.3186   0.04743   0.04149  -0.0873   0.6634   0.0286
  -2.000   0.3704   0.04798   0.04171  -0.0930   0.6560   0.0292
  -1.750   0.3875   0.04332   0.03712  -0.0938   0.6489   0.0299
  -1.500   0.4126   0.04058   0.03427  -0.0954   0.6430   0.0315
  -1.250   0.4449   0.03875   0.03234  -0.0978   0.6357   0.0336
  -1.000   0.4793   0.03727   0.03069  -0.1003   0.6296   0.0362
  -0.750   0.5217   0.03717   0.03035  -0.1032   0.6226   0.0386
  -0.500   0.5617   0.03703   0.02994  -0.1054   0.6165   0.0391
  -0.250   0.5869   0.03379   0.02668  -0.1069   0.6107   0.0399
   0.000   0.6144   0.03170   0.02452  -0.1082   0.6047   0.0416
   0.250   0.6453   0.03041   0.02306  -0.1095   0.5997   0.0438
   0.500   0.6781   0.02938   0.02191  -0.1108   0.5932   0.0469
   0.750   0.7180   0.03020   0.02238  -0.1116   0.5878   0.0505
   1.000   0.7413   0.02739   0.01961  -0.1128   0.5825   0.0564
   1.250   0.7782   0.02796   0.01989  -0.1132   0.5766   0.0622
   1.750   0.8362   0.02501   0.01675  -0.1147   0.5662   0.0643
   2.000   0.8690   0.02376   0.01523  -0.1149   0.5613   0.0367
   2.250   0.8991   0.02294   0.01421  -0.1151   0.5568   0.0340
   2.500   0.9294   0.02221   0.01333  -0.1152   0.5510   0.0323
   2.750   0.9592   0.02146   0.01235  -0.1151   0.5462   0.0313
   3.000   0.9882   0.02086   0.01157  -0.1150   0.5415   0.0322
   3.250   1.0167   0.02032   0.01085  -0.1147   0.5359   0.0385
   3.500   1.0459   0.01992   0.01026  -0.1148   0.5313   0.0439
   3.750   1.0746   0.01940   0.00951  -0.1146   0.5261   0.0543
   4.000   1.1006   0.01963   0.00981  -0.1144   0.5205   0.0929
   4.250   1.1268   0.01958   0.00956  -0.1139   0.5161   0.1107
   4.500   1.1526   0.01966   0.00967  -0.1136   0.5100   0.1205
   4.750   1.1785   0.01977   0.00973  -0.1133   0.5046   0.1331
   5.000   1.2044   0.01994   0.00989  -0.1130   0.4996   0.1534
   5.250   1.2300   0.02016   0.01025  -0.1127   0.4930   0.1755
   5.500   1.2560   0.02029   0.01036  -0.1123   0.4878   0.2083
   5.750   1.2813   0.02051   0.01079  -0.1121   0.4801   0.2629
   6.000   1.3077   0.02004   0.01092  -0.1119   0.4739   1.0000
   6.250   1.3323   0.02039   0.01137  -0.1115   0.4656   1.0000
   6.500   1.3575   0.02059   0.01154  -0.1109   0.4591   1.0000
   6.750   1.3817   0.02093   0.01212  -0.1104   0.4496   1.0000
   7.000   1.4060   0.02119   0.01248  -0.1099   0.4406   1.0000
   7.250   1.4304   0.02138   0.01272  -0.1092   0.4315   1.0000
   7.500   1.4539   0.02170   0.01323  -0.1086   0.4202   1.0000
   7.750   1.4772   0.02200   0.01370  -0.1080   0.4083   1.0000
   8.000   1.5004   0.02230   0.01426  -0.1073   0.3952   1.0000
   8.250   1.5230   0.02261   0.01475  -0.1066   0.3801   1.0000
   8.500   1.5448   0.02296   0.01524  -0.1057   0.3630   1.0000
   8.750   1.5657   0.02344   0.01591  -0.1048   0.3421   1.0000
   9.000   1.5834   0.02407   0.01654  -0.1036   0.3066   1.0000
   9.250   1.5951   0.02534   0.01754  -0.1021   0.2497   1.0000
   9.500   1.6037   0.02709   0.01906  -0.1004   0.2033   1.0000
   9.750   1.6080   0.02920   0.02106  -0.0984   0.1628   1.0000
  10.000   1.6049   0.03188   0.02343  -0.0961   0.1194   1.0000
  10.250   1.5988   0.03454   0.02588  -0.0935   0.0878   1.0000
  10.500   1.5872   0.03740   0.02858  -0.0907   0.0640   1.0000
  10.750   1.5765   0.04065   0.03175  -0.0890   0.0454   1.0000
  11.000   1.5656   0.04434   0.03540  -0.0880   0.0317   1.0000
  11.250   1.5550   0.04834   0.03940  -0.0874   0.0228   1.0000
  11.500   1.5479   0.05219   0.04339  -0.0871   0.0188   1.0000
  11.750   1.5401   0.05627   0.04761  -0.0870   0.0165   1.0000
  12.000   1.5310   0.06067   0.05214  -0.0871   0.0150   1.0000
  12.250   1.5210   0.06534   0.05695  -0.0875   0.0140   1.0000
  12.500   1.5137   0.06975   0.06159  -0.0879   0.0134   1.0000
  12.750   1.5057   0.07436   0.06641  -0.0885   0.0128   1.0000
  13.000   1.4975   0.07908   0.07134  -0.0892   0.0124   1.0000
  13.250   1.4892   0.08393   0.07639  -0.0901   0.0121   1.0000
  13.500   1.4813   0.08890   0.08156  -0.0911   0.0117   1.0000
  13.750   1.4741   0.09389   0.08674  -0.0922   0.0114   1.0000
  14.000   1.4674   0.09886   0.09190  -0.0934   0.0111   1.0000
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