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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 500,000
Max Cl/Cd: 138.99 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e385-il-500000.txt
Download as CSV file: xf-e385-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2703   0.11768   0.11544  -0.0377   1.0000   0.0114
  -9.750  -0.2710   0.11552   0.11331  -0.0375   1.0000   0.0114
  -9.500  -0.2737   0.11357   0.11140  -0.0368   1.0000   0.0115
  -9.250  -0.2610   0.10991   0.10774  -0.0405   0.9986   0.0115
  -9.000  -0.2434   0.10578   0.10361  -0.0453   0.9963   0.0115
  -8.750  -0.2251   0.10169   0.09952  -0.0500   0.9937   0.0115
  -8.500  -0.2099   0.09682   0.09466  -0.0519   0.9912   0.0118
  -8.250  -0.1912   0.09330   0.09113  -0.0549   0.9883   0.0122
  -8.000  -0.1708   0.08951   0.08734  -0.0597   0.9854   0.0123
  -7.750  -0.1534   0.08605   0.08389  -0.0636   0.9797   0.0126
  -7.500  -0.1336   0.08234   0.08018  -0.0683   0.9743   0.0133
  -7.250  -0.1156   0.07876   0.07660  -0.0726   0.9661   0.0135
  -7.000  -0.0928   0.07464   0.07246  -0.0787   0.9587   0.0144
  -6.750  -0.0654   0.06997   0.06778  -0.0881   0.9455   0.0154
  -6.500  -0.0303   0.06485   0.06261  -0.0995   0.9312   0.0157
  -6.250   0.0010   0.06001   0.05769  -0.1087   0.9134   0.0158
  -6.000   0.0137   0.05667   0.05430  -0.1098   0.8965   0.0170
  -5.750   0.0349   0.05372   0.05124  -0.1140   0.8770   0.0178
  -5.500   0.0567   0.05031   0.04770  -0.1191   0.8589   0.0188
  -5.250   0.0850   0.04573   0.04298  -0.1267   0.8424   0.0205
  -5.000   0.1264   0.03994   0.03692  -0.1366   0.8284   0.0214
  -4.750   0.1415   0.03620   0.03309  -0.1391   0.8161   0.0228
  -4.500   0.1672   0.03380   0.03055  -0.1416   0.8048   0.0240
  -4.250   0.1982   0.03041   0.02694  -0.1453   0.7948   0.0258
  -4.000   0.2378   0.02768   0.02370  -0.1486   0.7860   0.0289
  -3.750   0.2663   0.02254   0.01831  -0.1526   0.7771   0.0310
  -3.500   0.2948   0.02106   0.01666  -0.1537   0.7690   0.0329
  -3.250   0.3262   0.01965   0.01494  -0.1547   0.7609   0.0371
  -3.000   0.3681   0.01323   0.00746  -0.1572   0.7547   0.0191
  -2.750   0.3996   0.01143   0.00524  -0.1577   0.7473   0.0175
  -2.500   0.4290   0.01071   0.00438  -0.1580   0.7405   0.0182
  -2.250   0.4581   0.01019   0.00376  -0.1582   0.7332   0.0192
  -2.000   0.4867   0.00999   0.00345  -0.1583   0.7268   0.0211
  -1.750   0.5165   0.00948   0.00287  -0.1587   0.7200   0.0219
  -1.500   0.5461   0.00916   0.00243  -0.1590   0.7141   0.0248
  -1.250   0.5758   0.00885   0.00215  -0.1593   0.7075   0.0438
  -1.000   0.6053   0.00849   0.00207  -0.1600   0.7016   0.1544
  -0.750   0.6345   0.00822   0.00209  -0.1605   0.6957   0.2715
  -0.500   0.6640   0.00780   0.00217  -0.1613   0.6896   0.4727
  -0.250   0.6921   0.00742   0.00229  -0.1615   0.6844   0.6894
   0.000   0.7103   0.00700   0.00236  -0.1591   0.6786   0.8892
   0.250   0.7359   0.00695   0.00227  -0.1584   0.6730   1.0000
   0.500   0.7643   0.00705   0.00229  -0.1585   0.6676   1.0000
   0.750   0.7927   0.00713   0.00231  -0.1586   0.6619   1.0000
   1.000   0.8210   0.00727   0.00233  -0.1587   0.6568   1.0000
   1.250   0.8492   0.00735   0.00239  -0.1588   0.6511   1.0000
   1.500   0.8773   0.00745   0.00244  -0.1589   0.6455   1.0000
   1.750   0.9053   0.00758   0.00251  -0.1589   0.6403   1.0000
   2.000   0.9332   0.00766   0.00258  -0.1590   0.6341   1.0000
   2.250   0.9609   0.00779   0.00264  -0.1590   0.6282   1.0000
   2.500   0.9886   0.00788   0.00274  -0.1590   0.6213   1.0000
   2.750   1.0161   0.00799   0.00282  -0.1589   0.6146   1.0000
   3.000   1.0436   0.00810   0.00292  -0.1589   0.6079   1.0000
   3.250   1.0709   0.00821   0.00301  -0.1588   0.6008   1.0000
   3.500   1.0981   0.00832   0.00314  -0.1587   0.5933   1.0000
   3.750   1.1251   0.00844   0.00325  -0.1586   0.5856   1.0000
   4.000   1.1522   0.00855   0.00338  -0.1585   0.5779   1.0000
   4.250   1.1790   0.00869   0.00351  -0.1584   0.5702   1.0000
   4.500   1.2058   0.00879   0.00367  -0.1582   0.5611   1.0000
   4.750   1.2322   0.00894   0.00382  -0.1580   0.5517   1.0000
   5.000   1.2584   0.00909   0.00398  -0.1577   0.5415   1.0000
   5.250   1.2843   0.00924   0.00414  -0.1574   0.5283   1.0000
   5.500   1.3093   0.00943   0.00432  -0.1569   0.5094   1.0000
   5.750   1.3331   0.00970   0.00452  -0.1562   0.4837   1.0000
   6.000   1.3561   0.01006   0.00478  -0.1555   0.4498   1.0000
   6.250   1.3778   0.01055   0.00513  -0.1545   0.4119   1.0000
   6.500   1.3971   0.01128   0.00562  -0.1532   0.3585   1.0000
   6.750   1.4128   0.01237   0.00634  -0.1515   0.2911   1.0000
   7.000   1.4266   0.01362   0.00719  -0.1495   0.2235   1.0000
   7.250   1.4407   0.01481   0.00805  -0.1476   0.1665   1.0000
   7.500   1.4521   0.01619   0.00906  -0.1452   0.1081   1.0000
   7.750   1.4595   0.01779   0.01026  -0.1423   0.0505   1.0000
   8.000   1.4669   0.01929   0.01153  -0.1392   0.0193   1.0000
   8.250   1.4802   0.02022   0.01248  -0.1369   0.0152   1.0000
   8.500   1.4924   0.02104   0.01339  -0.1344   0.0140   1.0000
   8.750   1.5036   0.02189   0.01433  -0.1319   0.0132   1.0000
   9.000   1.5133   0.02285   0.01541  -0.1292   0.0126   1.0000
   9.250   1.5215   0.02396   0.01661  -0.1264   0.0121   1.0000
   9.500   1.5277   0.02526   0.01800  -0.1236   0.0116   1.0000
   9.750   1.5316   0.02679   0.01964  -0.1207   0.0113   1.0000
  10.000   1.5327   0.02864   0.02160  -0.1177   0.0109   1.0000
  10.250   1.5307   0.03091   0.02399  -0.1148   0.0106   1.0000
  10.500   1.5274   0.03347   0.02669  -0.1120   0.0104   1.0000
  10.750   1.5337   0.03525   0.02858  -0.1104   0.0102   1.0000
  11.000   1.5376   0.03737   0.03081  -0.1087   0.0100   1.0000
  11.250   1.5406   0.03969   0.03324  -0.1070   0.0099   1.0000
  11.500   1.5437   0.04211   0.03580  -0.1055   0.0098   1.0000
  11.750   1.5471   0.04458   0.03839  -0.1041   0.0097   1.0000
  12.000   1.5508   0.04712   0.04106  -0.1028   0.0096   1.0000
  12.250   1.5549   0.04972   0.04378  -0.1016   0.0095   1.0000
  12.500   1.5593   0.05238   0.04658  -0.1004   0.0094   1.0000
  12.750   1.5641   0.05512   0.04947  -0.0993   0.0093   1.0000
  13.000   1.5684   0.05801   0.05251  -0.0982   0.0092   1.0000
  13.250   1.5722   0.06112   0.05580  -0.0972   0.0092   1.0000
  13.500   1.5744   0.06456   0.05944  -0.0963   0.0091   1.0000
  13.750   1.5740   0.06845   0.06355  -0.0955   0.0092   1.0000
  14.000   1.5710   0.07250   0.06781  -0.0951   0.0091   1.0000
  14.250   1.5658   0.07689   0.07243  -0.0950   0.0090   1.0000
  14.500   1.5564   0.08220   0.07800  -0.0952   0.0090   1.0000
  14.750   1.5470   0.08737   0.08339  -0.0959   0.0090   1.0000
  15.000   1.5362   0.09291   0.08914  -0.0971   0.0090   1.0000
  15.250   1.5215   0.09937   0.09584  -0.0989   0.0090   1.0000
  15.500   1.5047   0.10644   0.10315  -0.1012   0.0091   1.0000
  15.750   1.4866   0.11407   0.11102  -0.1043   0.0093   1.0000
  16.000   1.4696   0.12175   0.11890  -0.1079   0.0094   1.0000
  16.250   1.4501   0.13035   0.12771  -0.1125   0.0096   1.0000
  16.500   1.4325   0.13889   0.13644  -0.1175   0.0097   1.0000
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