E385 (8.41%) (e385-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E385 (8.41%) (e385-il) Reynolds number: 500,000 Max Cl/Cd: 133.12 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e385-il-500000-n5.txt Download as CSV file: xf-e385-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2874 0.12974 0.12737 -0.0377 1.0000 0.0075
-11.000 -0.2834 0.12706 0.12471 -0.0380 1.0000 0.0075
-10.750 -0.2798 0.12440 0.12206 -0.0382 1.0000 0.0075
-10.500 -0.2704 0.12094 0.11862 -0.0403 0.9992 0.0076
-10.250 -0.2577 0.11645 0.11413 -0.0428 0.9976 0.0077
-10.000 -0.2439 0.11272 0.11039 -0.0455 0.9948 0.0078
-9.750 -0.2309 0.10935 0.10702 -0.0478 0.9919 0.0079
-9.500 -0.2175 0.10582 0.10350 -0.0508 0.9883 0.0080
-9.000 -0.1916 0.09917 0.09685 -0.0563 0.9777 0.0082
-8.500 -0.1633 0.09240 0.09009 -0.0626 0.9625 0.0087
-8.250 -0.1447 0.08866 0.08634 -0.0671 0.9530 0.0088
-8.000 -0.1199 0.08440 0.08204 -0.0736 0.9437 0.0091
-7.750 -0.0907 0.07964 0.07724 -0.0817 0.9297 0.0104
-7.500 -0.0612 0.07484 0.07235 -0.0908 0.9075 0.0108
-7.250 -0.0442 0.07103 0.06842 -0.0959 0.8785 0.0110
-7.000 -0.0357 0.06844 0.06573 -0.0974 0.8534 0.0109
-6.750 -0.0264 0.06541 0.06259 -0.0999 0.8319 0.0110
-6.500 -0.0154 0.06234 0.05945 -0.1027 0.8145 0.0110
-6.250 0.0069 0.04238 0.03947 -0.0923 0.7621 0.0118
-5.750 0.0255 0.05182 0.04873 -0.1141 0.7742 0.0116
-5.500 0.0434 0.05025 0.04711 -0.1157 0.7638 0.0126
-5.250 0.0667 0.04660 0.04337 -0.1210 0.7542 0.0133
-5.000 0.0942 0.04221 0.03887 -0.1274 0.7450 0.0136
-4.000 0.2450 0.01558 0.01002 -0.1524 0.7170 0.0075
-3.750 0.2765 0.01356 0.00753 -0.1537 0.7105 0.0077
-3.500 0.3066 0.01228 0.00597 -0.1545 0.7037 0.0080
-3.250 0.3356 0.01159 0.00511 -0.1549 0.6976 0.0084
-3.000 0.3647 0.01105 0.00445 -0.1552 0.6912 0.0089
-2.750 0.3936 0.01061 0.00387 -0.1555 0.6851 0.0094
-2.500 0.4224 0.01032 0.00350 -0.1557 0.6792 0.0104
-2.250 0.4511 0.01009 0.00318 -0.1559 0.6733 0.0111
-2.000 0.4806 0.00966 0.00265 -0.1563 0.6679 0.0115
-1.750 0.5098 0.00939 0.00232 -0.1566 0.6622 0.0123
-1.500 0.5385 0.00925 0.00209 -0.1568 0.6568 0.0136
-1.250 0.5672 0.00913 0.00190 -0.1570 0.6517 0.0156
-1.000 0.5963 0.00892 0.00178 -0.1573 0.6461 0.0433
-0.750 0.6250 0.00876 0.00173 -0.1576 0.6412 0.0938
-0.500 0.6538 0.00862 0.00171 -0.1579 0.6361 0.1465
-0.250 0.6828 0.00843 0.00173 -0.1584 0.6308 0.2398
0.000 0.7116 0.00824 0.00178 -0.1588 0.6260 0.3507
0.250 0.7407 0.00803 0.00185 -0.1593 0.6210 0.4735
0.500 0.7694 0.00777 0.00196 -0.1597 0.6157 0.6303
0.750 0.7956 0.00755 0.00207 -0.1593 0.6111 0.7742
1.000 0.8134 0.00720 0.00204 -0.1567 0.6061 1.0000
1.250 0.8415 0.00729 0.00207 -0.1568 0.6008 1.0000
1.500 0.8695 0.00740 0.00212 -0.1569 0.5959 1.0000
1.750 0.8977 0.00749 0.00218 -0.1570 0.5904 1.0000
2.000 0.9255 0.00760 0.00224 -0.1570 0.5846 1.0000
2.250 0.9532 0.00770 0.00231 -0.1570 0.5781 1.0000
2.500 0.9807 0.00782 0.00240 -0.1570 0.5704 1.0000
2.750 1.0083 0.00793 0.00249 -0.1570 0.5627 1.0000
3.000 1.0355 0.00806 0.00259 -0.1569 0.5550 1.0000
3.250 1.0629 0.00818 0.00270 -0.1569 0.5467 1.0000
3.500 1.0897 0.00833 0.00283 -0.1567 0.5373 1.0000
3.750 1.1167 0.00847 0.00296 -0.1566 0.5270 1.0000
4.000 1.1436 0.00862 0.00310 -0.1565 0.5174 1.0000
4.250 1.1701 0.00879 0.00327 -0.1563 0.5072 1.0000
4.500 1.1963 0.00899 0.00344 -0.1561 0.4948 1.0000
4.750 1.2222 0.00920 0.00363 -0.1558 0.4798 1.0000
5.000 1.2468 0.00950 0.00385 -0.1554 0.4541 1.0000
5.250 1.2698 0.00994 0.00415 -0.1546 0.4172 1.0000
5.500 1.2902 0.01064 0.00457 -0.1535 0.3624 1.0000
5.750 1.3063 0.01179 0.00526 -0.1519 0.2828 1.0000
6.000 1.3227 0.01291 0.00599 -0.1503 0.2152 1.0000
6.250 1.3402 0.01390 0.00670 -0.1489 0.1625 1.0000
6.500 1.3589 0.01474 0.00733 -0.1477 0.1256 1.0000
6.750 1.3766 0.01562 0.00802 -0.1463 0.0909 1.0000
7.000 1.3938 0.01651 0.00874 -0.1448 0.0605 1.0000
7.250 1.4088 0.01753 0.00959 -0.1430 0.0317 1.0000
7.500 1.4233 0.01854 0.01049 -0.1410 0.0128 1.0000
7.750 1.4410 0.01924 0.01121 -0.1395 0.0097 1.0000
8.000 1.4582 0.01991 0.01194 -0.1379 0.0086 1.0000
8.250 1.4735 0.02061 0.01271 -0.1360 0.0079 1.0000
8.500 1.4864 0.02137 0.01355 -0.1337 0.0075 1.0000
8.750 1.4993 0.02211 0.01437 -0.1315 0.0073 1.0000
9.000 1.5111 0.02294 0.01531 -0.1292 0.0071 1.0000
9.250 1.5218 0.02387 0.01633 -0.1268 0.0069 1.0000
9.500 1.5315 0.02491 0.01747 -0.1245 0.0067 1.0000
9.750 1.5402 0.02607 0.01872 -0.1221 0.0065 1.0000
10.000 1.5478 0.02736 0.02011 -0.1198 0.0064 1.0000
10.250 1.5545 0.02880 0.02165 -0.1176 0.0062 1.0000
10.500 1.5603 0.03038 0.02334 -0.1155 0.0061 1.0000
10.750 1.5653 0.03212 0.02519 -0.1135 0.0059 1.0000
11.000 1.5697 0.03399 0.02716 -0.1117 0.0058 1.0000
11.250 1.5733 0.03604 0.02931 -0.1100 0.0056 1.0000
11.500 1.5759 0.03828 0.03165 -0.1084 0.0054 1.0000
11.750 1.5766 0.04082 0.03431 -0.1070 0.0053 1.0000
12.000 1.5750 0.04372 0.03732 -0.1056 0.0051 1.0000
12.250 1.5723 0.04686 0.04058 -0.1043 0.0050 1.0000
12.500 1.5687 0.05025 0.04410 -0.1032 0.0049 1.0000
12.750 1.5686 0.05328 0.04725 -0.1024 0.0049 1.0000
13.000 1.5705 0.05616 0.05026 -0.1018 0.0049 1.0000
13.250 1.5721 0.05915 0.05339 -0.1013 0.0048 1.0000
13.500 1.5729 0.06232 0.05669 -0.1010 0.0048 1.0000
13.750 1.5734 0.06562 0.06013 -0.1007 0.0047 1.0000
14.000 1.5732 0.06911 0.06377 -0.1007 0.0047 1.0000
14.250 1.5727 0.07272 0.06752 -0.1007 0.0046 1.0000
14.500 1.5710 0.07660 0.07155 -0.1009 0.0046 1.0000
14.750 1.5691 0.08061 0.07571 -0.1013 0.0045 1.0000
15.000 1.5663 0.08487 0.08014 -0.1019 0.0044 1.0000
15.250 1.5627 0.08935 0.08478 -0.1027 0.0044 1.0000
15.500 1.5581 0.09408 0.08967 -0.1038 0.0043 1.0000
15.750 1.5529 0.09904 0.09480 -0.1051 0.0043 1.0000
16.000 1.5466 0.10434 0.10028 -0.1067 0.0043 1.0000
16.250 1.5399 0.10981 0.10592 -0.1086 0.0042 1.0000
16.500 1.5321 0.11562 0.11190 -0.1108 0.0042 1.0000
16.750 1.5233 0.12176 0.11824 -0.1135 0.0041 1.0000
17.000 1.5146 0.12807 0.12473 -0.1165 0.0041 1.0000
17.250 1.5050 0.13472 0.13155 -0.1199 0.0041 1.0000
17.500 1.4950 0.14173 0.13874 -0.1238 0.0040 1.0000
17.750 1.4843 0.14897 0.14615 -0.1280 0.0040 1.0000
18.000 1.4733 0.15655 0.15390 -0.1327 0.0041 1.0000
18.250 1.4623 0.16439 0.16191 -0.1378 0.0040 1.0000
18.500 1.4501 0.17290 0.17059 -0.1435 0.0041 1.0000
18.750 1.4376 0.18186 0.17971 -0.1496 0.0041 1.0000
19.000 1.4263 0.19089 0.18888 -0.1559 0.0041 1.0000
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