E392 (10.15%) (e392-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 50,000 Max Cl/Cd: 37.55 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e392-il-50000-n5.txt Download as CSV file: xf-e392-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3373 0.09414 0.08759 -0.0431 1.0000 0.0490
-8.000 -0.3364 0.09119 0.08470 -0.0426 1.0000 0.0485
-7.750 -0.3398 0.08847 0.08211 -0.0421 1.0000 0.0480
-7.500 -0.3456 0.08593 0.07970 -0.0414 1.0000 0.0475
-7.250 -0.3517 0.08324 0.07715 -0.0412 1.0000 0.0469
-7.000 -0.3589 0.08063 0.07467 -0.0410 1.0000 0.0462
-6.750 -0.3686 0.07800 0.07217 -0.0409 1.0000 0.0459
-6.500 -0.3787 0.07549 0.06975 -0.0406 1.0000 0.0454
-6.250 -0.3790 0.07174 0.06603 -0.0432 0.9970 0.0449
-6.000 -0.3514 0.06487 0.05898 -0.0531 0.9851 0.0441
-5.750 -0.3235 0.05827 0.05211 -0.0618 0.9734 0.0436
-5.500 -0.2946 0.05201 0.04544 -0.0692 0.9619 0.0426
-5.250 -0.2632 0.04632 0.03922 -0.0752 0.9517 0.0420
-5.000 -0.2268 0.04128 0.03353 -0.0805 0.9437 0.0420
-4.750 -0.1946 0.03751 0.02915 -0.0834 0.9338 0.0425
-4.500 -0.1580 0.03423 0.02523 -0.0863 0.9262 0.0442
-4.250 -0.1217 0.03169 0.02195 -0.0883 0.9181 0.0485
-4.000 -0.0873 0.02965 0.01965 -0.0900 0.9103 0.0531
-3.750 -0.0518 0.02786 0.01752 -0.0912 0.9029 0.0589
-3.500 -0.0201 0.02656 0.01605 -0.0920 0.8945 0.0702
-3.250 0.0147 0.02521 0.01454 -0.0932 0.8873 0.0913
-3.000 0.0448 0.02410 0.01344 -0.0938 0.8782 0.1291
-2.750 0.0802 0.02274 0.01238 -0.0957 0.8717 0.2058
-2.500 0.1070 0.02162 0.01194 -0.0961 0.8623 0.3468
-2.250 0.1342 0.02083 0.01178 -0.0954 0.8555 0.5385
-2.000 0.1525 0.02053 0.01177 -0.0926 0.8458 0.6665
-1.750 0.1709 0.02023 0.01164 -0.0892 0.8377 0.7809
-1.500 0.2127 0.01980 0.01115 -0.0904 0.8309 0.9483
-1.250 0.2485 0.01985 0.01078 -0.0924 0.8227 1.0000
-1.000 0.2789 0.01999 0.01056 -0.0932 0.8147 1.0000
-0.750 0.3062 0.02024 0.01051 -0.0936 0.8060 1.0000
-0.500 0.3375 0.02039 0.01037 -0.0943 0.7991 1.0000
-0.250 0.3630 0.02071 0.01046 -0.0943 0.7902 1.0000
0.000 0.3943 0.02087 0.01040 -0.0949 0.7839 1.0000
0.250 0.4187 0.02125 0.01061 -0.0947 0.7749 1.0000
0.500 0.4497 0.02143 0.01060 -0.0952 0.7689 1.0000
0.750 0.4731 0.02187 0.01093 -0.0949 0.7600 1.0000
1.000 0.5038 0.02206 0.01098 -0.0953 0.7542 1.0000
1.250 0.5265 0.02256 0.01141 -0.0949 0.7453 1.0000
1.500 0.5568 0.02278 0.01152 -0.0952 0.7397 1.0000
1.750 0.5790 0.02332 0.01203 -0.0948 0.7308 1.0000
2.000 0.6089 0.02356 0.01222 -0.0950 0.7252 1.0000
2.250 0.6306 0.02416 0.01281 -0.0945 0.7164 1.0000
2.500 0.6602 0.02440 0.01303 -0.0946 0.7107 1.0000
2.750 0.6814 0.02505 0.01370 -0.0940 0.7019 1.0000
3.000 0.7108 0.02530 0.01398 -0.0941 0.6962 1.0000
3.250 0.7313 0.02601 0.01473 -0.0935 0.6872 1.0000
3.500 0.7609 0.02625 0.01500 -0.0935 0.6814 1.0000
3.750 0.7806 0.02700 0.01584 -0.0928 0.6721 1.0000
4.000 0.8110 0.02718 0.01610 -0.0928 0.6663 1.0000
4.250 0.8296 0.02799 0.01703 -0.0919 0.6563 1.0000
4.500 0.8566 0.02832 0.01745 -0.0916 0.6491 1.0000
4.750 0.8793 0.02886 0.01815 -0.0910 0.6398 1.0000
5.000 0.9009 0.02946 0.01888 -0.0901 0.6300 1.0000
5.250 0.9318 0.02945 0.01899 -0.0899 0.6226 1.0000
5.500 0.9508 0.03011 0.01982 -0.0888 0.6109 1.0000
5.750 0.9723 0.03058 0.02050 -0.0877 0.5997 1.0000
6.000 0.9976 0.03076 0.02086 -0.0869 0.5889 1.0000
6.250 1.0271 0.03057 0.02084 -0.0862 0.5781 1.0000
6.500 1.0501 0.03073 0.02119 -0.0849 0.5647 1.0000
6.750 1.0732 0.03078 0.02149 -0.0836 0.5502 1.0000
7.000 1.0939 0.03089 0.02182 -0.0820 0.5339 1.0000
7.250 1.1114 0.03113 0.02230 -0.0801 0.5155 1.0000
7.500 1.1323 0.03103 0.02241 -0.0782 0.4959 1.0000
7.750 1.1501 0.03107 0.02266 -0.0761 0.4736 1.0000
8.000 1.1671 0.03108 0.02287 -0.0738 0.4477 1.0000
8.250 1.1791 0.03142 0.02337 -0.0711 0.4169 1.0000
8.500 1.1900 0.03182 0.02381 -0.0683 0.3800 1.0000
8.750 1.1962 0.03257 0.02447 -0.0651 0.3368 1.0000
9.000 1.1965 0.03384 0.02551 -0.0617 0.2931 1.0000
9.250 1.1929 0.03574 0.02715 -0.0585 0.2528 1.0000
9.500 1.1871 0.03813 0.02934 -0.0559 0.2171 1.0000
9.750 1.1793 0.04096 0.03193 -0.0539 0.1846 1.0000
10.000 1.1711 0.04410 0.03485 -0.0524 0.1556 1.0000
10.250 1.1641 0.04740 0.03798 -0.0514 0.1296 1.0000
10.500 1.1590 0.05073 0.04124 -0.0507 0.1080 1.0000
10.750 1.1544 0.05416 0.04459 -0.0501 0.0919 1.0000
11.000 1.1515 0.05753 0.04793 -0.0495 0.0795 1.0000
11.250 1.1505 0.06080 0.05122 -0.0489 0.0697 1.0000
11.500 1.1500 0.06405 0.05446 -0.0484 0.0630 1.0000
11.750 1.1548 0.06683 0.05739 -0.0475 0.0574 1.0000
12.000 1.1591 0.06963 0.06018 -0.0467 0.0536 1.0000
12.250 1.1709 0.07198 0.06284 -0.0455 0.0494 1.0000
12.500 1.1779 0.07474 0.06579 -0.0449 0.0460 1.0000
12.750 1.1857 0.07739 0.06843 -0.0443 0.0432 1.0000
13.000 1.1943 0.08058 0.07204 -0.0437 0.0413 1.0000
13.250 1.1990 0.08439 0.07622 -0.0435 0.0400 1.0000
13.500 1.1976 0.08887 0.08104 -0.0440 0.0392 1.0000
13.750 1.1914 0.09400 0.08648 -0.0451 0.0387 1.0000
14.000 1.1809 0.09978 0.09255 -0.0470 0.0383 1.0000
14.250 1.1668 0.10630 0.09935 -0.0498 0.0382 1.0000
14.500 1.1496 0.11372 0.10702 -0.0536 0.0383 1.0000
14.750 1.1297 0.12221 0.11573 -0.0584 0.0386 1.0000
15.000 1.1079 0.13196 0.12568 -0.0645 0.0390 1.0000
15.250 1.0851 0.14314 0.13695 -0.0716 0.0396 1.0000
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Polar data table (+)
Polar graphs
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