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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 1,000,000
Max Cl/Cd: 172.31 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e385-il-1000000.txt
Download as CSV file: xf-e385-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2864   0.12639   0.12474  -0.0348   1.0000   0.0064
 -10.750  -0.2830   0.12385   0.12221  -0.0348   1.0000   0.0065
 -10.500  -0.2802   0.12136   0.11974  -0.0347   1.0000   0.0067
 -10.250  -0.2737   0.11843   0.11682  -0.0358   0.9997   0.0069
 -10.000  -0.2583   0.11462   0.11301  -0.0394   0.9988   0.0071
  -9.750  -0.2432   0.11077   0.10915  -0.0431   0.9976   0.0073
  -9.500  -0.2274   0.10686   0.10524  -0.0470   0.9960   0.0077
  -5.000   0.1229   0.03291   0.03014  -0.1402   0.7644   0.0120
  -4.750   0.1493   0.03035   0.02743  -0.1431   0.7551   0.0124
  -4.500   0.1786   0.02726   0.02416  -0.1463   0.7461   0.0128
  -4.250   0.2097   0.02400   0.02066  -0.1492   0.7382   0.0139
  -4.000   0.2444   0.02106   0.01730  -0.1509   0.7304   0.0157
  -3.750   0.2775   0.01637   0.01214  -0.1547   0.7236   0.0170
  -3.500   0.3065   0.01536   0.01097  -0.1555   0.7163   0.0179
  -3.250   0.3366   0.01427   0.00967  -0.1562   0.7096   0.0195
  -3.000   0.3736   0.01034   0.00496  -0.1574   0.7034   0.0112
  -2.750   0.4036   0.00938   0.00381  -0.1578   0.6972   0.0111
  -2.500   0.4326   0.00905   0.00339  -0.1580   0.6908   0.0115
  -2.250   0.4629   0.00822   0.00241  -0.1587   0.6849   0.0127
  -2.000   0.4922   0.00795   0.00210  -0.1590   0.6790   0.0134
  -1.750   0.5211   0.00778   0.00187  -0.1592   0.6732   0.0144
  -1.500   0.5500   0.00765   0.00168  -0.1594   0.6678   0.0155
  -1.250   0.5792   0.00746   0.00142  -0.1596   0.6621   0.0175
  -1.000   0.6085   0.00724   0.00129  -0.1600   0.6568   0.0603
  -0.750   0.6377   0.00705   0.00126  -0.1604   0.6516   0.1219
  -0.500   0.6668   0.00686   0.00127  -0.1608   0.6462   0.2107
  -0.250   0.6957   0.00668   0.00131  -0.1613   0.6410   0.3184
   0.000   0.7254   0.00636   0.00139  -0.1620   0.6360   0.4868
   0.500   0.7820   0.00592   0.00158  -0.1624   0.6257   0.7800
   0.750   0.8011   0.00555   0.00157  -0.1602   0.6207   1.0000
   1.000   0.8293   0.00564   0.00160  -0.1603   0.6154   1.0000
   1.250   0.8576   0.00572   0.00163  -0.1604   0.6100   1.0000
   1.500   0.8858   0.00579   0.00167  -0.1605   0.6038   1.0000
   1.750   0.9136   0.00590   0.00171  -0.1605   0.5973   1.0000
   2.000   0.9419   0.00595   0.00176  -0.1606   0.5907   1.0000
   2.250   0.9695   0.00607   0.00182  -0.1606   0.5842   1.0000
   2.500   0.9977   0.00613   0.00189  -0.1607   0.5776   1.0000
   2.750   1.0252   0.00625   0.00195  -0.1607   0.5702   1.0000
   3.000   1.0530   0.00633   0.00203  -0.1607   0.5627   1.0000
   3.500   1.1082   0.00654   0.00222  -0.1607   0.5479   1.0000
   3.750   1.1353   0.00667   0.00232  -0.1607   0.5399   1.0000
   4.000   1.1627   0.00677   0.00242  -0.1607   0.5305   1.0000
   4.250   1.1898   0.00691   0.00254  -0.1606   0.5206   1.0000
   4.500   1.2165   0.00706   0.00268  -0.1605   0.5094   1.0000
   4.750   1.2428   0.00725   0.00282  -0.1603   0.4911   1.0000
   5.000   1.2680   0.00754   0.00300  -0.1599   0.4649   1.0000
   5.250   1.2927   0.00788   0.00322  -0.1594   0.4343   1.0000
   5.500   1.3161   0.00836   0.00352  -0.1588   0.3946   1.0000
   5.750   1.3364   0.00914   0.00398  -0.1578   0.3318   1.0000
   6.000   1.3557   0.01004   0.00454  -0.1566   0.2702   1.0000
   6.250   1.3749   0.01092   0.00512  -0.1554   0.2148   1.0000
   6.500   1.3931   0.01186   0.00576  -0.1540   0.1605   1.0000
   6.750   1.4095   0.01295   0.00650  -0.1524   0.1048   1.0000
   7.000   1.4252   0.01405   0.00730  -0.1506   0.0571   1.0000
   7.250   1.4380   0.01537   0.00832  -0.1484   0.0144   1.0000
   7.500   1.4581   0.01599   0.00895  -0.1471   0.0103   1.0000
   7.750   1.4789   0.01650   0.00951  -0.1461   0.0096   1.0000
   8.000   1.4987   0.01706   0.01013  -0.1449   0.0090   1.0000
   8.250   1.5171   0.01771   0.01082  -0.1434   0.0084   1.0000
   8.500   1.5335   0.01847   0.01165  -0.1416   0.0079   1.0000
   8.750   1.5457   0.01943   0.01273  -0.1391   0.0074   1.0000
   9.000   1.5550   0.02034   0.01373  -0.1361   0.0072   1.0000
   9.250   1.5666   0.02108   0.01453  -0.1336   0.0070   1.0000
   9.500   1.5760   0.02198   0.01551  -0.1309   0.0068   1.0000
   9.750   1.5840   0.02303   0.01664  -0.1281   0.0067   1.0000
  10.000   1.5910   0.02420   0.01791  -0.1253   0.0066   1.0000
  10.250   1.5970   0.02551   0.01931  -0.1226   0.0065   1.0000
  10.500   1.6023   0.02696   0.02085  -0.1201   0.0064   1.0000
  10.750   1.6068   0.02856   0.02255  -0.1176   0.0063   1.0000
  11.000   1.6108   0.03031   0.02439  -0.1154   0.0062   1.0000
  11.250   1.6143   0.03219   0.02638  -0.1133   0.0061   1.0000
  11.500   1.6174   0.03423   0.02852  -0.1114   0.0060   1.0000
  11.750   1.6203   0.03639   0.03077  -0.1097   0.0058   1.0000
  12.000   1.6229   0.03867   0.03314  -0.1081   0.0057   1.0000
  12.250   1.6250   0.04109   0.03566  -0.1067   0.0056   1.0000
  12.500   1.6265   0.04367   0.03834  -0.1055   0.0055   1.0000
  12.750   1.6276   0.04640   0.04117  -0.1043   0.0054   1.0000
  13.000   1.6278   0.04931   0.04418  -0.1033   0.0053   1.0000
  13.250   1.6270   0.05243   0.04739  -0.1024   0.0052   1.0000
  13.500   1.6243   0.05594   0.05102  -0.1014   0.0051   1.0000
  13.750   1.6188   0.06015   0.05537  -0.1002   0.0049   1.0000
  14.000   1.6130   0.06474   0.06017  -0.0991   0.0048   1.0000
  14.250   1.6126   0.06802   0.06359  -0.0992   0.0047   1.0000
  14.500   1.6104   0.07181   0.06754  -0.0993   0.0047   1.0000
  14.750   1.6070   0.07592   0.07180  -0.0995   0.0047   1.0000
  15.000   1.6027   0.08028   0.07631  -0.1001   0.0046   1.0000
  15.250   1.5976   0.08486   0.08105  -0.1009   0.0046   1.0000
  15.500   1.5903   0.08993   0.08628  -0.1019   0.0046   1.0000
  15.750   1.5814   0.09546   0.09199  -0.1033   0.0045   1.0000
  16.000   1.5724   0.10113   0.09783  -0.1051   0.0045   1.0000
  16.250   1.5595   0.10773   0.10462  -0.1073   0.0045   1.0000
  16.500   1.5482   0.11418   0.11123  -0.1100   0.0045   1.0000
  16.750   1.5366   0.12088   0.11810  -0.1131   0.0045   1.0000
  17.000   1.5255   0.12777   0.12514  -0.1166   0.0045   1.0000
  17.250   1.5093   0.13590   0.13346  -0.1209   0.0045   1.0000
  17.500   1.4996   0.14291   0.14061  -0.1250   0.0044   1.0000
  17.750   1.4828   0.15181   0.14968  -0.1305   0.0045   1.0000
  18.000   1.4681   0.16044   0.15846  -0.1360   0.0045   1.0000
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