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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 500,000
Max Cl/Cd: 136.42 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e395-il-500000.txt
Download as CSV file: xf-e395-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2812   0.12665   0.12441  -0.0524   0.9966   0.0173
 -11.500  -0.2668   0.12279   0.12055  -0.0559   0.9951   0.0177
 -11.250  -0.3946   0.07999   0.07762  -0.0744   0.9918   0.0075
 -11.000  -0.4165   0.06800   0.06554  -0.0854   0.9870   0.0073
 -10.750  -0.4312   0.05648   0.05385  -0.0985   0.9819   0.0071
 -10.500  -0.4411   0.04590   0.04306  -0.1120   0.9722   0.0070
 -10.250  -0.4412   0.03643   0.03331  -0.1267   0.9597   0.0070
 -10.000  -0.4206   0.02892   0.02534  -0.1423   0.9488   0.0070
  -9.750  -0.3885   0.02493   0.02093  -0.1502   0.9452   0.0070
  -9.500  -0.3638   0.02257   0.01825  -0.1531   0.9365   0.0072
  -9.250  -0.3298   0.02059   0.01600  -0.1569   0.9323   0.0074
  -9.000  -0.3032   0.01854   0.01372  -0.1591   0.9239   0.0077
  -8.750  -0.2709   0.01710   0.01213  -0.1617   0.9177   0.0083
  -8.500  -0.2433   0.01617   0.01106  -0.1626   0.9092   0.0088
  -8.250  -0.2123   0.01527   0.00997  -0.1641   0.9024   0.0097
  -8.000  -0.1866   0.01427   0.00883  -0.1646   0.8935   0.0106
  -7.750  -0.1567   0.01358   0.00800  -0.1656   0.8867   0.0122
  -7.500  -0.1308   0.01284   0.00717  -0.1657   0.8784   0.0148
  -7.250  -0.1016   0.01220   0.00643  -0.1664   0.8719   0.0212
  -7.000  -0.0750   0.01175   0.00598  -0.1666   0.8643   0.0290
  -6.750  -0.0464   0.01143   0.00561  -0.1670   0.8579   0.0368
  -6.500  -0.0189   0.01113   0.00528  -0.1672   0.8513   0.0446
  -6.250   0.0091   0.01085   0.00497  -0.1674   0.8449   0.0532
  -6.000   0.0377   0.01061   0.00467  -0.1677   0.8392   0.0625
  -5.750   0.0653   0.01038   0.00440  -0.1678   0.8327   0.0720
  -5.500   0.0941   0.01017   0.00414  -0.1681   0.8273   0.0829
  -5.250   0.1221   0.00992   0.00389  -0.1683   0.8215   0.0961
  -5.000   0.1502   0.00971   0.00367  -0.1685   0.8158   0.1104
  -4.500   0.2072   0.00935   0.00330  -0.1690   0.8052   0.1426
  -4.250   0.2356   0.00920   0.00315  -0.1693   0.7999   0.1595
  -4.000   0.2648   0.00909   0.00302  -0.1696   0.7953   0.1776
  -3.750   0.2926   0.00897   0.00293  -0.1697   0.7899   0.1965
  -3.500   0.3211   0.00888   0.00283  -0.1699   0.7849   0.2150
  -3.250   0.3504   0.00881   0.00275  -0.1702   0.7804   0.2343
  -3.000   0.3782   0.00872   0.00269  -0.1703   0.7753   0.2534
  -2.750   0.4066   0.00865   0.00264  -0.1705   0.7703   0.2731
  -2.500   0.4357   0.00863   0.00258  -0.1708   0.7660   0.2928
  -2.250   0.4637   0.00856   0.00256  -0.1709   0.7611   0.3121
  -2.000   0.4920   0.00850   0.00254  -0.1710   0.7561   0.3321
  -1.750   0.5209   0.00848   0.00251  -0.1712   0.7517   0.3528
  -1.500   0.5492   0.00845   0.00251  -0.1714   0.7470   0.3737
  -1.250   0.5773   0.00840   0.00252  -0.1715   0.7419   0.3958
  -0.750   0.6343   0.00837   0.00254  -0.1718   0.7328   0.4439
  -0.500   0.6622   0.00834   0.00258  -0.1719   0.7277   0.4697
  -0.250   0.6906   0.00832   0.00260  -0.1720   0.7230   0.4972
   0.000   0.7191   0.00833   0.00265  -0.1722   0.7185   0.5261
   0.250   0.7467   0.00830   0.00272  -0.1722   0.7131   0.5562
   0.500   0.7747   0.00828   0.00277  -0.1722   0.7083   0.5875
   0.750   0.8030   0.00830   0.00284  -0.1723   0.7036   0.6202
   1.250   0.8576   0.00826   0.00300  -0.1721   0.6929   0.6895
   1.500   0.8848   0.00828   0.00309  -0.1719   0.6878   0.7272
   1.750   0.9108   0.00825   0.00320  -0.1715   0.6817   0.7660
   2.000   0.9365   0.00824   0.00327  -0.1709   0.6763   0.8081
   2.500   0.9775   0.00809   0.00339  -0.1673   0.6640   0.9212
   2.750   1.0049   0.00810   0.00339  -0.1672   0.6579   1.0000
   3.000   1.0320   0.00817   0.00347  -0.1671   0.6505   1.0000
   3.250   1.0598   0.00829   0.00354  -0.1671   0.6438   1.0000
   3.500   1.0863   0.00836   0.00364  -0.1669   0.6358   1.0000
   3.750   1.1133   0.00849   0.00372  -0.1668   0.6284   1.0000
   4.000   1.1394   0.00858   0.00384  -0.1665   0.6195   1.0000
   4.250   1.1656   0.00871   0.00396  -0.1662   0.6111   1.0000
   4.500   1.1914   0.00883   0.00408  -0.1658   0.6018   1.0000
   4.750   1.2169   0.00896   0.00422  -0.1654   0.5921   1.0000
   5.000   1.2420   0.00912   0.00437  -0.1649   0.5818   1.0000
   5.250   1.2663   0.00929   0.00453  -0.1643   0.5700   1.0000
   5.500   1.2905   0.00946   0.00471  -0.1636   0.5574   1.0000
   5.750   1.3139   0.00966   0.00491  -0.1628   0.5436   1.0000
   6.000   1.3366   0.00990   0.00513  -0.1618   0.5285   1.0000
   6.250   1.3581   0.01017   0.00537  -0.1607   0.5114   1.0000
   6.500   1.3788   0.01048   0.00564  -0.1594   0.4930   1.0000
   6.750   1.3984   0.01083   0.00594  -0.1579   0.4711   1.0000
   7.000   1.4154   0.01127   0.00630  -0.1559   0.4462   1.0000
   7.250   1.4300   0.01180   0.00671  -0.1536   0.4165   1.0000
   7.500   1.4405   0.01242   0.00719  -0.1504   0.3832   1.0000
   7.750   1.4488   0.01313   0.00775  -0.1470   0.3494   1.0000
   8.000   1.4564   0.01393   0.00839  -0.1435   0.3163   1.0000
   8.250   1.4635   0.01481   0.00911  -0.1401   0.2842   1.0000
   8.500   1.4696   0.01577   0.00991  -0.1367   0.2511   1.0000
   8.750   1.4750   0.01682   0.01081  -0.1333   0.2196   1.0000
   9.000   1.4798   0.01795   0.01178  -0.1300   0.1899   1.0000
   9.250   1.4845   0.01916   0.01284  -0.1268   0.1626   1.0000
   9.500   1.4893   0.02042   0.01398  -0.1238   0.1389   1.0000
   9.750   1.4947   0.02171   0.01517  -0.1211   0.1169   1.0000
  10.000   1.4996   0.02309   0.01647  -0.1184   0.0984   1.0000
  10.250   1.5051   0.02451   0.01781  -0.1160   0.0814   1.0000
  10.500   1.5097   0.02605   0.01929  -0.1136   0.0666   1.0000
  10.750   1.5144   0.02765   0.02084  -0.1114   0.0544   1.0000
  11.000   1.5187   0.02936   0.02251  -0.1092   0.0440   1.0000
  11.250   1.5232   0.03112   0.02426  -0.1073   0.0356   1.0000
  11.500   1.5280   0.03291   0.02606  -0.1054   0.0294   1.0000
  11.750   1.5326   0.03479   0.02796  -0.1037   0.0245   1.0000
  12.000   1.5356   0.03687   0.03008  -0.1020   0.0206   1.0000
  12.250   1.5384   0.03905   0.03228  -0.1004   0.0174   1.0000
  12.500   1.5430   0.04112   0.03444  -0.0991   0.0150   1.0000
  12.750   1.5425   0.04379   0.03714  -0.0976   0.0131   1.0000
  13.000   1.5479   0.04590   0.03935  -0.0965   0.0116   1.0000
  13.250   1.5486   0.04859   0.04212  -0.0954   0.0105   1.0000
  13.500   1.5483   0.05152   0.04516  -0.0944   0.0095   1.0000
  13.750   1.5510   0.05417   0.04790  -0.0937   0.0087   1.0000
  14.000   1.5513   0.05718   0.05099  -0.0931   0.0080   1.0000
  14.250   1.5442   0.06125   0.05516  -0.0925   0.0075   1.0000
  14.500   1.5468   0.06417   0.05821  -0.0922   0.0070   1.0000
  14.750   1.5476   0.06739   0.06154  -0.0920   0.0065   1.0000
  15.000   1.5483   0.07070   0.06494  -0.0920   0.0061   1.0000
  15.250   1.5449   0.07469   0.06902  -0.0922   0.0058   1.0000
  15.500   1.5327   0.08010   0.07454  -0.0927   0.0055   1.0000
  15.750   1.5339   0.08363   0.07822  -0.0931   0.0053   1.0000
  16.000   1.5327   0.08759   0.08231  -0.0937   0.0051   1.0000
  16.250   1.5305   0.09179   0.08663  -0.0946   0.0048   1.0000
  16.500   1.5277   0.09617   0.09113  -0.0956   0.0046   1.0000
  16.750   1.5238   0.10079   0.09587  -0.0968   0.0045   1.0000
  17.000   1.5192   0.10559   0.10077  -0.0982   0.0043   1.0000
  17.250   1.5137   0.11063   0.10592  -0.0999   0.0042   1.0000
  17.500   1.5073   0.11589   0.11129  -0.1017   0.0041   1.0000
  17.750   1.4999   0.12134   0.11686  -0.1038   0.0040   1.0000
  18.000   1.4919   0.12692   0.12255  -0.1061   0.0040   1.0000
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