E385 (8.41%) (e385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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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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Polar data table (+)
Polar graphs
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