E385 (8.41%) (e385-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E385 (8.41%) (e385-il) Reynolds number: 100,000 Max Cl/Cd: 68.84 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e385-il-100000-n5.txt Download as CSV file: xf-e385-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2734 0.12588 0.12091 -0.0420 1.0000 0.0351
-9.750 -0.2766 0.12481 0.11990 -0.0427 1.0000 0.0353
-9.500 -0.2791 0.12333 0.11851 -0.0429 1.0000 0.0354
-9.250 -0.2818 0.12176 0.11703 -0.0426 1.0000 0.0355
-9.000 -0.2627 0.11370 0.10896 -0.0396 1.0000 0.0368
-8.750 -0.2606 0.11105 0.10637 -0.0382 1.0000 0.0375
-8.500 -0.2621 0.10909 0.10449 -0.0367 1.0000 0.0382
-8.250 -0.2664 0.10757 0.10305 -0.0349 0.9999 0.0387
-8.000 -0.2470 0.10365 0.09913 -0.0394 0.9943 0.0401
-7.750 -0.2286 0.09991 0.09540 -0.0440 0.9875 0.0416
-7.500 -0.2113 0.09640 0.09188 -0.0486 0.9793 0.0431
-7.250 -0.1945 0.09309 0.08858 -0.0542 0.9696 0.0450
-7.000 -0.1798 0.09064 0.08616 -0.0620 0.9545 0.0464
-6.750 -0.1546 0.08701 0.08252 -0.0729 0.9422 0.0470
-6.500 -0.1267 0.08271 0.07816 -0.0823 0.9328 0.0472
-6.250 -0.1134 0.07755 0.07304 -0.0830 0.9247 0.0479
-6.000 -0.0946 0.07343 0.06891 -0.0834 0.9190 0.0489
-5.750 -0.0751 0.06999 0.06544 -0.0859 0.9097 0.0500
-5.500 -0.0472 0.06597 0.06137 -0.0917 0.9030 0.0513
-5.250 -0.0232 0.06227 0.05762 -0.0970 0.8921 0.0523
-5.000 0.0223 0.05479 0.04990 -0.1114 0.8819 0.0347
-4.750 0.0585 0.04812 0.04305 -0.1201 0.8750 0.0280
-4.500 0.0926 0.04359 0.03829 -0.1260 0.8655 0.0265
-4.250 0.1361 0.03822 0.03254 -0.1339 0.8597 0.0266
-4.000 0.1736 0.03370 0.02758 -0.1393 0.8506 0.0267
-3.750 0.2150 0.02968 0.02305 -0.1444 0.8451 0.0263
-3.500 0.2507 0.02653 0.01938 -0.1474 0.8364 0.0259
-3.250 0.2901 0.02371 0.01594 -0.1503 0.8307 0.0259
-3.000 0.3229 0.02175 0.01346 -0.1516 0.8222 0.0261
-2.750 0.3578 0.02010 0.01135 -0.1528 0.8162 0.0268
-2.500 0.3873 0.01899 0.01006 -0.1533 0.8078 0.0286
-2.250 0.4190 0.01826 0.00917 -0.1540 0.8016 0.0332
-2.000 0.4480 0.01747 0.00822 -0.1541 0.7934 0.0364
-1.750 0.4797 0.01677 0.00740 -0.1548 0.7873 0.0429
-1.500 0.5087 0.01619 0.00682 -0.1550 0.7794 0.0659
-1.250 0.5394 0.01546 0.00652 -0.1559 0.7733 0.1832
-1.000 0.5679 0.01499 0.00641 -0.1564 0.7659 0.3317
-0.750 0.5957 0.01443 0.00638 -0.1564 0.7597 0.5494
-0.500 0.6076 0.01379 0.00637 -0.1521 0.7529 0.8245
-0.250 0.6347 0.01372 0.00614 -0.1516 0.7461 1.0000
0.000 0.6638 0.01388 0.00605 -0.1518 0.7400 1.0000
0.250 0.6919 0.01406 0.00604 -0.1519 0.7332 1.0000
0.500 0.7214 0.01421 0.00598 -0.1521 0.7279 1.0000
0.750 0.7483 0.01444 0.00610 -0.1521 0.7206 1.0000
1.000 0.7771 0.01460 0.00612 -0.1522 0.7151 1.0000
1.250 0.8043 0.01483 0.00626 -0.1522 0.7085 1.0000
1.500 0.8322 0.01504 0.00638 -0.1522 0.7024 1.0000
1.750 0.8602 0.01525 0.00651 -0.1522 0.6968 1.0000
2.000 0.8869 0.01550 0.00673 -0.1521 0.6901 1.0000
2.250 0.9154 0.01569 0.00684 -0.1522 0.6850 1.0000
2.500 0.9414 0.01597 0.00714 -0.1520 0.6780 1.0000
2.750 0.9689 0.01619 0.00735 -0.1520 0.6722 1.0000
3.000 0.9957 0.01646 0.00762 -0.1518 0.6660 1.0000
3.250 1.0222 0.01672 0.00790 -0.1516 0.6594 1.0000
3.500 1.0497 0.01694 0.00812 -0.1516 0.6535 1.0000
3.750 1.0750 0.01724 0.00852 -0.1512 0.6458 1.0000
4.000 1.1026 0.01743 0.00872 -0.1511 0.6395 1.0000
4.250 1.1273 0.01772 0.00910 -0.1506 0.6306 1.0000
4.500 1.1537 0.01793 0.00940 -0.1503 0.6228 1.0000
4.750 1.1792 0.01816 0.00970 -0.1498 0.6140 1.0000
5.000 1.2040 0.01841 0.01006 -0.1492 0.6045 1.0000
5.250 1.2300 0.01858 0.01029 -0.1488 0.5951 1.0000
5.500 1.2544 0.01879 0.01064 -0.1480 0.5840 1.0000
5.750 1.2780 0.01903 0.01103 -0.1472 0.5722 1.0000
6.000 1.3018 0.01925 0.01138 -0.1464 0.5598 1.0000
6.250 1.3252 0.01947 0.01173 -0.1455 0.5461 1.0000
6.500 1.3480 0.01969 0.01211 -0.1445 0.5305 1.0000
6.750 1.3702 0.01992 0.01246 -0.1434 0.5130 1.0000
7.000 1.3913 0.02021 0.01287 -0.1420 0.4931 1.0000
7.250 1.4110 0.02055 0.01331 -0.1405 0.4692 1.0000
7.500 1.4276 0.02100 0.01378 -0.1385 0.4335 1.0000
7.750 1.4383 0.02178 0.01434 -0.1355 0.3753 1.0000
8.000 1.4410 0.02320 0.01527 -0.1317 0.3038 1.0000
8.250 1.4407 0.02497 0.01662 -0.1279 0.2430 1.0000
8.500 1.4397 0.02673 0.01809 -0.1241 0.1955 1.0000
8.750 1.4368 0.02862 0.01970 -0.1202 0.1520 1.0000
9.000 1.4346 0.03060 0.02146 -0.1168 0.1149 1.0000
9.250 1.4334 0.03266 0.02336 -0.1137 0.0840 1.0000
9.500 1.4310 0.03498 0.02551 -0.1108 0.0578 1.0000
9.750 1.4291 0.03741 0.02786 -0.1083 0.0410 1.0000
10.000 1.4282 0.03990 0.03041 -0.1060 0.0329 1.0000
10.250 1.4282 0.04242 0.03303 -0.1040 0.0287 1.0000
10.500 1.4270 0.04518 0.03589 -0.1022 0.0263 1.0000
10.750 1.4279 0.04781 0.03873 -0.1007 0.0246 1.0000
11.000 1.4281 0.05061 0.04172 -0.0994 0.0233 1.0000
11.250 1.4278 0.05356 0.04484 -0.0983 0.0223 1.0000
11.500 1.4269 0.05665 0.04809 -0.0973 0.0215 1.0000
11.750 1.4252 0.05994 0.05151 -0.0964 0.0208 1.0000
12.000 1.4221 0.06348 0.05518 -0.0956 0.0201 1.0000
12.250 1.4243 0.06647 0.05835 -0.0949 0.0194 1.0000
12.500 1.4270 0.06948 0.06160 -0.0942 0.0185 1.0000
12.750 1.4295 0.07258 0.06489 -0.0937 0.0177 1.0000
13.000 1.4317 0.07577 0.06825 -0.0933 0.0170 1.0000
13.250 1.4343 0.07902 0.07167 -0.0929 0.0165 1.0000
13.500 1.4370 0.08237 0.07520 -0.0925 0.0162 1.0000
13.750 1.4392 0.08584 0.07885 -0.0923 0.0159 1.0000
14.000 1.4404 0.08952 0.08272 -0.0923 0.0156 1.0000
14.250 1.4409 0.09342 0.08681 -0.0924 0.0154 1.0000
14.500 1.4400 0.09760 0.09120 -0.0928 0.0152 1.0000
14.750 1.4372 0.10216 0.09598 -0.0935 0.0151 1.0000
15.000 1.4320 0.10721 0.10127 -0.0947 0.0149 1.0000
15.250 1.4241 0.11278 0.10709 -0.0966 0.0149 1.0000
15.500 1.4147 0.11870 0.11331 -0.0990 0.0149 1.0000
15.750 1.4041 0.12503 0.11990 -0.1020 0.0149 1.0000
16.000 1.3918 0.13198 0.12710 -0.1058 0.0149 1.0000
16.250 1.3795 0.13918 0.13453 -0.1100 0.0149 1.0000
16.500 1.3666 0.14695 0.14251 -0.1149 0.0149 1.0000
16.750 1.3513 0.15582 0.15164 -0.1210 0.0150 1.0000
17.000 1.3317 0.16711 0.16318 -0.1293 0.0152 1.0000
17.250 1.2985 0.18509 0.18142 -0.1424 0.0158 1.0000
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Polar data table (+)
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