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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 1,000,000
Max Cl/Cd: 159.87 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e385-il-1000000-n5.txt
Download as CSV file: xf-e385-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E385  (8.41%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0524   0.08301   0.08108  -0.0806   0.8897   0.0056
  -9.500  -0.0475   0.08006   0.07800  -0.0812   0.8622   0.0056
  -9.250  -0.0428   0.07722   0.07505  -0.0817   0.8393   0.0057
  -9.000  -0.0382   0.07424   0.07200  -0.0823   0.8204   0.0057
  -8.750  -0.0338   0.07125   0.06895  -0.0828   0.8050   0.0058
  -8.500  -0.0285   0.06837   0.06601  -0.0836   0.7907   0.0063
  -8.250  -0.0240   0.06534   0.06294  -0.0842   0.7786   0.0061
  -8.000  -0.0191   0.06233   0.05988  -0.0850   0.7666   0.0070
  -7.750  -0.0166   0.05882   0.05634  -0.0863   0.7566   0.0074
  -7.500  -0.0121   0.05585   0.05334  -0.0871   0.7466   0.0074
  -7.000  -0.0401   0.06659   0.06403  -0.0963   0.7629   0.0054
  -6.750  -0.0307   0.06465   0.06204  -0.0976   0.7513   0.0059
  -6.500  -0.0208   0.06183   0.05919  -0.1002   0.7405   0.0062
  -6.250  -0.0087   0.05849   0.05582  -0.1038   0.7309   0.0067
  -6.000   0.0063   0.05486   0.05215  -0.1083   0.7218   0.0067
  -5.500   0.0474   0.04654   0.04373  -0.1200   0.7061   0.0063
  -5.000   0.1064   0.03608   0.03303  -0.1345   0.6924   0.0066
  -4.750   0.1655   0.01434   0.00973  -0.1528   0.6884   0.0052
  -4.500   0.1962   0.01260   0.00759  -0.1540   0.6826   0.0052
  -4.250   0.2261   0.01152   0.00626  -0.1548   0.6766   0.0053
  -4.000   0.2554   0.01077   0.00532  -0.1553   0.6706   0.0054
  -3.750   0.2847   0.01020   0.00460  -0.1557   0.6651   0.0056
  -3.500   0.3138   0.00974   0.00402  -0.1561   0.6593   0.0058
  -3.250   0.3428   0.00935   0.00352  -0.1564   0.6541   0.0062
  -3.000   0.3720   0.00901   0.00309  -0.1567   0.6488   0.0066
  -2.750   0.4009   0.00874   0.00274  -0.1570   0.6433   0.0070
  -2.500   0.4298   0.00853   0.00246  -0.1572   0.6387   0.0073
  -2.250   0.4587   0.00834   0.00222  -0.1574   0.6336   0.0075
  -2.000   0.4880   0.00805   0.00186  -0.1578   0.6283   0.0084
  -1.750   0.5168   0.00790   0.00167  -0.1580   0.6238   0.0090
  -1.500   0.5457   0.00778   0.00150  -0.1582   0.6190   0.0096
  -1.250   0.5743   0.00770   0.00136  -0.1584   0.6139   0.0105
  -1.000   0.6029   0.00763   0.00125  -0.1585   0.6093   0.0120
  -0.750   0.6317   0.00753   0.00117  -0.1587   0.6046   0.0236
  -0.500   0.6606   0.00739   0.00115  -0.1590   0.5995   0.0700
  -0.250   0.6893   0.00729   0.00114  -0.1593   0.5950   0.1147
   0.000   0.7181   0.00719   0.00115  -0.1596   0.5902   0.1650
   0.250   0.7469   0.00706   0.00118  -0.1600   0.5851   0.2427
   0.500   0.7757   0.00694   0.00124  -0.1604   0.5804   0.3298
   0.750   0.8049   0.00674   0.00132  -0.1609   0.5753   0.4572
   1.000   0.8335   0.00665   0.00139  -0.1612   0.5697   0.5444
   1.250   0.8621   0.00654   0.00148  -0.1615   0.5643   0.6384
   1.500   0.8900   0.00637   0.00160  -0.1616   0.5568   0.7701
   1.750   0.9098   0.00612   0.00167  -0.1597   0.5496   0.9319
   2.000   0.9368   0.00615   0.00169  -0.1595   0.5412   1.0000
   2.250   0.9647   0.00625   0.00175  -0.1595   0.5337   1.0000
   2.500   0.9922   0.00638   0.00183  -0.1595   0.5250   1.0000
   2.750   1.0199   0.00649   0.00191  -0.1595   0.5151   1.0000
   3.000   1.0473   0.00662   0.00200  -0.1595   0.5048   1.0000
   3.250   1.0744   0.00677   0.00211  -0.1595   0.4947   1.0000
   3.500   1.1017   0.00691   0.00222  -0.1594   0.4841   1.0000
   3.750   1.1287   0.00706   0.00234  -0.1593   0.4724   1.0000
   4.000   1.1553   0.00726   0.00248  -0.1592   0.4571   1.0000
   4.250   1.1810   0.00754   0.00267  -0.1589   0.4329   1.0000
   4.500   1.2044   0.00806   0.00295  -0.1583   0.3858   1.0000
   4.750   1.2255   0.00883   0.00338  -0.1574   0.3211   1.0000
   5.000   1.2447   0.00980   0.00394  -0.1562   0.2472   1.0000
   5.500   1.2870   0.01126   0.00490  -0.1544   0.1544   1.0000
   5.750   1.3079   0.01198   0.00540  -0.1534   0.1147   1.0000
   6.000   1.3278   0.01277   0.00596  -0.1523   0.0746   1.0000
   6.250   1.3481   0.01350   0.00653  -0.1513   0.0459   1.0000
   6.500   1.3684   0.01420   0.00710  -0.1502   0.0236   1.0000
   6.750   1.3879   0.01494   0.00774  -0.1489   0.0081   1.0000
   7.000   1.4107   0.01534   0.00817  -0.1482   0.0070   1.0000
   7.250   1.4330   0.01576   0.00863  -0.1474   0.0065   1.0000
   7.500   1.4546   0.01622   0.00913  -0.1465   0.0060   1.0000
   7.750   1.4755   0.01672   0.00966  -0.1455   0.0057   1.0000
   8.000   1.4955   0.01727   0.01026  -0.1444   0.0053   1.0000
   8.250   1.5141   0.01789   0.01094  -0.1430   0.0051   1.0000
   8.500   1.5318   0.01854   0.01165  -0.1415   0.0049   1.0000
   8.750   1.5494   0.01914   0.01231  -0.1400   0.0048   1.0000
   9.000   1.5643   0.01976   0.01299  -0.1379   0.0047   1.0000
   9.250   1.5769   0.02044   0.01373  -0.1355   0.0046   1.0000
   9.500   1.5886   0.02117   0.01453  -0.1331   0.0045   1.0000
   9.750   1.5999   0.02197   0.01539  -0.1307   0.0043   1.0000
  10.000   1.6103   0.02285   0.01634  -0.1283   0.0042   1.0000
  10.250   1.6202   0.02382   0.01739  -0.1260   0.0040   1.0000
  10.500   1.6289   0.02492   0.01857  -0.1236   0.0039   1.0000
  10.750   1.6368   0.02613   0.01986  -0.1214   0.0038   1.0000
  11.000   1.6441   0.02745   0.02126  -0.1192   0.0037   1.0000
  11.250   1.6508   0.02890   0.02279  -0.1171   0.0037   1.0000
  11.500   1.6569   0.03047   0.02444  -0.1152   0.0036   1.0000
  11.750   1.6623   0.03218   0.02624  -0.1134   0.0035   1.0000
  12.000   1.6671   0.03402   0.02818  -0.1117   0.0035   1.0000
  12.250   1.6709   0.03605   0.03030  -0.1101   0.0034   1.0000
  12.500   1.6739   0.03825   0.03260  -0.1087   0.0033   1.0000
  12.750   1.6757   0.04067   0.03512  -0.1074   0.0033   1.0000
  13.000   1.6761   0.04333   0.03789  -0.1062   0.0032   1.0000
  13.250   1.6751   0.04626   0.04093  -0.1051   0.0032   1.0000
  13.500   1.6718   0.04958   0.04437  -0.1042   0.0031   1.0000
  13.750   1.6670   0.05319   0.04811  -0.1035   0.0031   1.0000
  14.000   1.6598   0.05729   0.05235  -0.1029   0.0030   1.0000
  14.250   1.6543   0.06131   0.05649  -0.1026   0.0030   1.0000
  14.500   1.6527   0.06490   0.06020  -0.1026   0.0030   1.0000
  14.750   1.6521   0.06846   0.06388  -0.1027   0.0029   1.0000
  15.000   1.6511   0.07219   0.06772  -0.1030   0.0029   1.0000
  15.250   1.6487   0.07621   0.07188  -0.1034   0.0029   1.0000
  15.500   1.6451   0.08053   0.07633  -0.1041   0.0029   1.0000
  15.750   1.6405   0.08512   0.08105  -0.1050   0.0029   1.0000
  16.000   1.6361   0.08982   0.08588  -0.1061   0.0028   1.0000
  16.250   1.6312   0.09470   0.09088  -0.1074   0.0028   1.0000
  16.500   1.6240   0.10009   0.09642  -0.1090   0.0028   1.0000
  16.750   1.6178   0.10542   0.10188  -0.1108   0.0027   1.0000
  17.000   1.6108   0.11104   0.10764  -0.1128   0.0027   1.0000
  17.250   1.6030   0.11690   0.11363  -0.1152   0.0027   1.0000
  17.500   1.5975   0.12246   0.11932  -0.1177   0.0026   1.0000
  17.750   1.5876   0.12891   0.12591  -0.1206   0.0026   1.0000
  18.000   1.5796   0.13515   0.13228  -0.1237   0.0026   1.0000
  18.250   1.5707   0.14170   0.13897  -0.1272   0.0026   1.0000
  18.500   1.5600   0.14878   0.14619  -0.1312   0.0026   1.0000
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