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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 100,000
Max Cl/Cd: 59.77 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e395-il-100000.txt
Download as CSV file: xf-e395-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 395 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3194   0.10103   0.09699  -0.0457   0.9756   0.1168
  -7.250  -0.3245   0.09834   0.09433  -0.0504   0.9681   0.1232
  -7.000  -0.3412   0.09466   0.09073  -0.0615   0.9571   0.1248
  -6.750  -0.3737   0.06196   0.05770  -0.0888   0.9480   0.0580
  -6.500  -0.3564   0.05303   0.04837  -0.0986   0.9428   0.0569
  -6.250  -0.3296   0.04352   0.03782  -0.1090   0.9376   0.0575
  -6.000  -0.2954   0.04070   0.03481  -0.1130   0.9337   0.0644
  -5.750  -0.2492   0.03620   0.02947  -0.1197   0.9313   0.0740
  -5.500  -0.2216   0.03422   0.02697  -0.1212   0.9257   0.0842
  -5.250  -0.1866   0.03283   0.02525  -0.1235   0.9212   0.0973
  -5.000  -0.1462   0.03152   0.02378  -0.1265   0.9178   0.1127
  -4.750  -0.1168   0.03076   0.02286  -0.1275   0.9129   0.1270
  -4.500  -0.0874   0.03008   0.02208  -0.1285   0.9074   0.1422
  -4.250  -0.0489   0.02946   0.02142  -0.1308   0.9036   0.1618
  -4.000  -0.0149   0.02906   0.02081  -0.1324   0.8993   0.1839
  -3.750   0.0087   0.02884   0.02065  -0.1322   0.8929   0.2031
  -3.500   0.0470   0.02855   0.02025  -0.1344   0.8889   0.2307
  -3.250   0.0804   0.02839   0.02018  -0.1358   0.8847   0.2563
  -3.000   0.1016   0.02846   0.02023  -0.1352   0.8777   0.2795
  -2.750   0.1392   0.02830   0.02007  -0.1371   0.8737   0.3103
  -2.500   0.1686   0.02837   0.02014  -0.1378   0.8687   0.3381
  -2.250   0.1911   0.02851   0.02036  -0.1373   0.8619   0.3628
  -2.000   0.2293   0.02839   0.02027  -0.1391   0.8582   0.3960
  -1.750   0.2517   0.02866   0.02057  -0.1387   0.8519   0.4230
  -1.500   0.2785   0.02879   0.02075  -0.1388   0.8459   0.4532
  -1.250   0.3176   0.02863   0.02067  -0.1406   0.8425   0.4895
  -1.000   0.3322   0.02915   0.02124  -0.1389   0.8346   0.5169
  -0.750   0.3637   0.02916   0.02136  -0.1395   0.8296   0.5540
  -0.500   0.4042   0.02892   0.02123  -0.1413   0.8268   0.5982
  -0.250   0.4109   0.02968   0.02209  -0.1383   0.8173   0.6295
   0.000   0.4452   0.02952   0.02206  -0.1389   0.8133   0.6798
   0.250   0.4821   0.02918   0.02187  -0.1396   0.8106   0.7387
   0.500   0.4795   0.03002   0.02287  -0.1349   0.7999   0.7884
   1.000   0.5193   0.03032   0.02329  -0.1324   0.7864   1.0000
   1.250   0.5638   0.03032   0.02310  -0.1355   0.7828   1.0000
   1.500   0.6103   0.03016   0.02281  -0.1385   0.7801   1.0000
   1.750   0.6161   0.03148   0.02406  -0.1362   0.7689   1.0000
   2.000   0.6628   0.03117   0.02366  -0.1389   0.7664   1.0000
   2.250   0.6677   0.03259   0.02505  -0.1364   0.7551   1.0000
   2.500   0.7125   0.03226   0.02466  -0.1387   0.7521   1.0000
   2.750   0.7607   0.03172   0.02409  -0.1414   0.7500   1.0000
   3.000   0.7625   0.03329   0.02565  -0.1384   0.7377   1.0000
   3.250   0.8120   0.03256   0.02493  -0.1410   0.7357   1.0000
   3.500   0.8142   0.03417   0.02654  -0.1382   0.7233   1.0000
   3.750   0.8638   0.03330   0.02570  -0.1406   0.7212   1.0000
   4.000   0.8676   0.03485   0.02727  -0.1379   0.7089   1.0000
   4.250   0.9183   0.03377   0.02623  -0.1403   0.7067   1.0000
   4.500   0.9756   0.03245   0.02499  -0.1437   0.7052   1.0000
   4.750   0.9760   0.03393   0.02650  -0.1401   0.6922   1.0000
   5.000   0.9864   0.03500   0.02763  -0.1379   0.6810   1.0000
   5.250   1.0397   0.03355   0.02629  -0.1404   0.6780   1.0000
   5.500   1.1029   0.03167   0.02451  -0.1443   0.6760   1.0000
   5.750   1.1115   0.03255   0.02547  -0.1415   0.6638   1.0000
   6.000   1.1755   0.03044   0.02350  -0.1453   0.6610   1.0000
   6.250   1.1915   0.03083   0.02399  -0.1432   0.6492   1.0000
   6.500   1.2575   0.02851   0.02180  -0.1472   0.6450   1.0000
   6.750   1.2759   0.02862   0.02203  -0.1453   0.6325   1.0000
   7.000   1.3030   0.02824   0.02177  -0.1444   0.6206   1.0000
   7.250   1.3400   0.02729   0.02095  -0.1447   0.6090   1.0000
   7.500   1.3758   0.02634   0.02011  -0.1447   0.5957   1.0000
   7.750   1.4034   0.02577   0.01963  -0.1437   0.5799   1.0000
   8.000   1.4269   0.02536   0.01932  -0.1421   0.5622   1.0000
   8.250   1.4514   0.02489   0.01893  -0.1405   0.5426   1.0000
   8.500   1.4684   0.02478   0.01887  -0.1380   0.5207   1.0000
   8.750   1.4822   0.02480   0.01892  -0.1350   0.4962   1.0000
   9.000   1.4871   0.02517   0.01932  -0.1307   0.4700   1.0000
   9.250   1.4906   0.02570   0.01981  -0.1264   0.4416   1.0000
   9.500   1.4910   0.02650   0.02056  -0.1219   0.4108   1.0000
   9.750   1.4884   0.02761   0.02155  -0.1173   0.3785   1.0000
  10.000   1.4836   0.02906   0.02284  -0.1129   0.3453   1.0000
  10.250   1.4765   0.03086   0.02448  -0.1086   0.3119   1.0000
  10.500   1.4683   0.03298   0.02644  -0.1047   0.2791   1.0000
  10.750   1.4596   0.03540   0.02867  -0.1011   0.2478   1.0000
  11.000   1.4505   0.03807   0.03117  -0.0980   0.2184   1.0000
  11.250   1.4415   0.04096   0.03389  -0.0952   0.1912   1.0000
  11.500   1.4324   0.04408   0.03680  -0.0926   0.1672   1.0000
  11.750   1.4250   0.04726   0.03988  -0.0905   0.1441   1.0000
  12.000   1.4183   0.05056   0.04298  -0.0886   0.1253   1.0000
  12.250   1.4142   0.05378   0.04618  -0.0869   0.1079   1.0000
  12.500   1.4118   0.05696   0.04930  -0.0854   0.0938   1.0000
  12.750   1.4116   0.06006   0.05237  -0.0841   0.0820   1.0000
  13.000   1.4141   0.06302   0.05527  -0.0829   0.0721   1.0000
  13.250   1.4213   0.06571   0.05780  -0.0817   0.0630   1.0000
  13.500   1.4232   0.06878   0.06114  -0.0809   0.0568   1.0000
  13.750   1.4367   0.07132   0.06365  -0.0797   0.0505   1.0000
  14.000   1.4401   0.07439   0.06691  -0.0789   0.0462   1.0000
  14.250   1.4553   0.07718   0.06969  -0.0780   0.0418   1.0000
  14.500   1.4595   0.08078   0.07366  -0.0772   0.0395   1.0000
  14.750   1.4609   0.08432   0.07741  -0.0768   0.0374   1.0000
  15.000   1.4758   0.08775   0.08076  -0.0764   0.0344   1.0000
  15.250   1.4623   0.09242   0.08582  -0.0765   0.0338   1.0000
  15.500   1.4494   0.09753   0.09129  -0.0771   0.0331   1.0000
  15.750   1.4364   0.10301   0.09711  -0.0780   0.0327   1.0000
  16.000   1.4216   0.10892   0.10335  -0.0795   0.0325   1.0000
  16.250   1.4052   0.11524   0.10997  -0.0817   0.0325   1.0000
  16.500   1.3873   0.12204   0.11705  -0.0846   0.0325   1.0000
  16.750   1.3683   0.12932   0.12460  -0.0883   0.0326   1.0000
  17.000   1.3489   0.13705   0.13257  -0.0926   0.0329   1.0000
  17.250   1.3287   0.14543   0.14116  -0.0978   0.0332   1.0000
  17.500   1.3088   0.15430   0.15022  -0.1037   0.0335   1.0000
  17.750   1.2902   0.16350   0.15956  -0.1100   0.0339   1.0000
  18.000   1.2737   0.17283   0.16899  -0.1163   0.0343   1.0000
  18.250   1.2048   0.20486   0.20112  -0.1380   0.0428   1.0000
  18.500   1.1901   0.22399   0.22017  -0.1475   0.0529   1.0000
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