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
|
Polar data table (+)
Polar graphs
<< Back to E385 (8.41%) (e385-il)