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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 200,000
Max Cl/Cd: 92 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e395-il-200000-n5.txt
Download as CSV file: xf-e395-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3491   0.08168   0.07813  -0.0768   0.9831   0.0098
 -10.250  -0.4000   0.05914   0.05540  -0.0955   0.9610   0.0091
 -10.000  -0.4201   0.04895   0.04502  -0.1062   0.9469   0.0086
  -9.750  -0.4239   0.03817   0.03388  -0.1226   0.9327   0.0085
  -9.500  -0.4040   0.03240   0.02765  -0.1338   0.9228   0.0091
  -9.250  -0.3763   0.02886   0.02365  -0.1401   0.9175   0.0098
  -9.000  -0.3521   0.02671   0.02128  -0.1430   0.9101   0.0105
  -8.750  -0.3223   0.02500   0.01936  -0.1461   0.9048   0.0114
  -8.500  -0.2909   0.02317   0.01723  -0.1490   0.9001   0.0124
  -8.250  -0.2649   0.02164   0.01547  -0.1504   0.8926   0.0134
  -8.000  -0.2324   0.02033   0.01397  -0.1528   0.8880   0.0149
  -7.750  -0.2040   0.01916   0.01261  -0.1541   0.8816   0.0172
  -7.500  -0.1739   0.01828   0.01158  -0.1554   0.8756   0.0211
  -7.250  -0.1411   0.01744   0.01062  -0.1571   0.8711   0.0266
  -7.000  -0.1146   0.01683   0.00990  -0.1575   0.8639   0.0325
  -6.750  -0.0837   0.01624   0.00919  -0.1586   0.8586   0.0398
  -6.500  -0.0545   0.01575   0.00860  -0.1593   0.8529   0.0476
  -6.000   0.0048   0.01478   0.00749  -0.1608   0.8419   0.0647
  -5.750   0.0323   0.01441   0.00705  -0.1610   0.8357   0.0742
  -5.500   0.0613   0.01408   0.00663  -0.1615   0.8301   0.0849
  -5.250   0.0918   0.01376   0.00622  -0.1622   0.8255   0.0973
  -5.000   0.1189   0.01350   0.00593  -0.1622   0.8193   0.1100
  -4.750   0.1480   0.01325   0.00562  -0.1627   0.8141   0.1245
  -4.500   0.1776   0.01302   0.00535  -0.1632   0.8094   0.1405
  -4.250   0.2050   0.01284   0.00516  -0.1633   0.8036   0.1566
  -4.000   0.2341   0.01266   0.00495  -0.1637   0.7986   0.1742
  -3.750   0.2633   0.01251   0.00477  -0.1640   0.7941   0.1923
  -3.500   0.2908   0.01239   0.00465  -0.1641   0.7884   0.2107
  -3.250   0.3197   0.01229   0.00451  -0.1644   0.7836   0.2299
  -3.000   0.3489   0.01219   0.00439  -0.1647   0.7792   0.2487
  -2.750   0.3762   0.01211   0.00433  -0.1647   0.7736   0.2676
  -2.500   0.4048   0.01204   0.00424  -0.1649   0.7688   0.2870
  -2.250   0.4342   0.01198   0.00415  -0.1653   0.7647   0.3071
  -2.000   0.4612   0.01194   0.00414  -0.1652   0.7591   0.3263
  -1.750   0.4895   0.01189   0.00411  -0.1653   0.7542   0.3466
  -1.500   0.5189   0.01185   0.00405  -0.1657   0.7503   0.3685
  -1.250   0.5458   0.01184   0.00409  -0.1655   0.7447   0.3897
  -1.000   0.5737   0.01181   0.00410  -0.1656   0.7397   0.4125
  -0.750   0.6028   0.01179   0.00409  -0.1659   0.7356   0.4363
  -0.500   0.6296   0.01179   0.00416  -0.1657   0.7301   0.4608
  -0.250   0.6572   0.01178   0.00421  -0.1657   0.7250   0.4865
   0.000   0.6859   0.01177   0.00424  -0.1658   0.7207   0.5141
   0.250   0.7125   0.01179   0.00434  -0.1657   0.7153   0.5425
   0.500   0.7395   0.01179   0.00443  -0.1655   0.7099   0.5724
   0.750   0.7675   0.01179   0.00448  -0.1654   0.7055   0.6044
   1.000   0.7932   0.01181   0.00463  -0.1650   0.6997   0.6369
   1.250   0.8193   0.01182   0.00474  -0.1646   0.6943   0.6712
   1.500   0.8463   0.01183   0.00480  -0.1643   0.6898   0.7082
   1.750   0.8698   0.01185   0.00497  -0.1634   0.6835   0.7467
   2.000   0.8935   0.01184   0.00507  -0.1623   0.6779   0.7890
   2.250   0.9158   0.01182   0.00514  -0.1609   0.6727   0.8385
   2.500   0.9339   0.01174   0.00520  -0.1586   0.6662   0.9130
   2.750   0.9632   0.01176   0.00521  -0.1588   0.6605   1.0000
   3.000   0.9897   0.01191   0.00537  -0.1587   0.6535   1.0000
   3.250   1.0171   0.01204   0.00547  -0.1587   0.6467   1.0000
   3.500   1.0436   0.01218   0.00564  -0.1585   0.6394   1.0000
   3.750   1.0703   0.01232   0.00577  -0.1583   0.6318   1.0000
   4.000   1.0960   0.01247   0.00594  -0.1580   0.6234   1.0000
   4.250   1.1224   0.01262   0.00608  -0.1577   0.6151   1.0000
   4.500   1.1470   0.01278   0.00629  -0.1571   0.6052   1.0000
   4.750   1.1722   0.01295   0.00646  -0.1566   0.5956   1.0000
   5.000   1.1969   0.01313   0.00665  -0.1560   0.5851   1.0000
   5.250   1.2205   0.01333   0.00688  -0.1553   0.5734   1.0000
   5.500   1.2439   0.01354   0.00712  -0.1545   0.5614   1.0000
   5.750   1.2669   0.01377   0.00736  -0.1536   0.5485   1.0000
   6.000   1.2889   0.01403   0.00764  -0.1525   0.5341   1.0000
   6.250   1.3099   0.01431   0.00793  -0.1512   0.5179   1.0000
   6.500   1.3298   0.01464   0.00824  -0.1498   0.4999   1.0000
   6.750   1.3480   0.01503   0.00859  -0.1480   0.4802   1.0000
   7.000   1.3647   0.01546   0.00900  -0.1461   0.4580   1.0000
   7.250   1.3787   0.01598   0.00945  -0.1436   0.4340   1.0000
   7.500   1.3893   0.01656   0.00995  -0.1406   0.4075   1.0000
   7.750   1.3977   0.01725   0.01055  -0.1373   0.3799   1.0000
   8.000   1.4040   0.01807   0.01127  -0.1338   0.3507   1.0000
   8.250   1.4085   0.01904   0.01212  -0.1301   0.3204   1.0000
   8.500   1.4120   0.02014   0.01309  -0.1265   0.2904   1.0000
   8.750   1.4147   0.02137   0.01420  -0.1231   0.2611   1.0000
   9.000   1.4172   0.02271   0.01542  -0.1198   0.2330   1.0000
   9.250   1.4197   0.02416   0.01675  -0.1167   0.2066   1.0000
   9.500   1.4222   0.02570   0.01819  -0.1139   0.1823   1.0000
   9.750   1.4261   0.02725   0.01967  -0.1114   0.1595   1.0000
  10.000   1.4294   0.02893   0.02129  -0.1090   0.1395   1.0000
  10.250   1.4338   0.03061   0.02292  -0.1069   0.1209   1.0000
  10.500   1.4376   0.03240   0.02467  -0.1049   0.1039   1.0000
  10.750   1.4410   0.03431   0.02652  -0.1030   0.0888   1.0000
  11.000   1.4443   0.03629   0.02848  -0.1012   0.0753   1.0000
  11.250   1.4477   0.03833   0.03050  -0.0996   0.0636   1.0000
  11.500   1.4512   0.04042   0.03259  -0.0981   0.0535   1.0000
  11.750   1.4549   0.04257   0.03478  -0.0967   0.0452   1.0000
  12.000   1.4584   0.04479   0.03704  -0.0954   0.0386   1.0000
  12.250   1.4609   0.04719   0.03948  -0.0942   0.0333   1.0000
  12.500   1.4637   0.04964   0.04198  -0.0931   0.0287   1.0000
  12.750   1.4663   0.05217   0.04460  -0.0922   0.0252   1.0000
  13.000   1.4676   0.05492   0.04741  -0.0913   0.0223   1.0000
  13.250   1.4695   0.05769   0.05029  -0.0906   0.0198   1.0000
  13.500   1.4704   0.06066   0.05335  -0.0900   0.0178   1.0000
  13.750   1.4700   0.06387   0.05667  -0.0896   0.0162   1.0000
  14.000   1.4710   0.06699   0.05994  -0.0893   0.0146   1.0000
  14.250   1.4696   0.07051   0.06354  -0.0892   0.0134   1.0000
  14.500   1.4688   0.07406   0.06723  -0.0892   0.0123   1.0000
  14.750   1.4676   0.07773   0.07105  -0.0893   0.0114   1.0000
  15.000   1.4652   0.08166   0.07511  -0.0897   0.0108   1.0000
  15.250   1.4605   0.08604   0.07961  -0.0903   0.0102   1.0000
  15.500   1.4566   0.09043   0.08415  -0.0910   0.0097   1.0000
  15.750   1.4536   0.09476   0.08864  -0.0919   0.0092   1.0000
  16.000   1.4504   0.09917   0.09320  -0.0929   0.0087   1.0000
  16.250   1.4471   0.10369   0.09785  -0.0942   0.0082   1.0000
  16.500   1.4428   0.10846   0.10275  -0.0958   0.0078   1.0000
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