S2091-101-83 (s2091-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 100,000 Max Cl/Cd: 57.92 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2091-il-100000-n5.txt Download as CSV file: xf-s2091-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2091-101-83
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3352 0.09656 0.09170 -0.0347 1.0000 0.0347
-8.750 -0.3255 0.09380 0.08897 -0.0342 1.0000 0.0340
-8.250 -0.3196 0.08720 0.08248 -0.0361 1.0000 0.0325
-8.000 -0.3206 0.08396 0.07933 -0.0371 1.0000 0.0319
-7.750 -0.3276 0.08092 0.07641 -0.0375 1.0000 0.0313
-7.500 -0.3446 0.07898 0.07462 -0.0357 1.0000 0.0309
-7.000 -0.3225 0.05694 0.05240 -0.0656 0.9719 0.0284
-6.750 -0.3023 0.04845 0.04359 -0.0752 0.9599 0.0286
-6.500 -0.2745 0.04826 0.04342 -0.0768 0.9516 0.0304
-6.250 -0.2507 0.04141 0.03608 -0.0835 0.9417 0.0317
-6.000 -0.2288 0.03514 0.02910 -0.0875 0.9311 0.0329
-5.750 -0.2056 0.03026 0.02338 -0.0894 0.9211 0.0340
-5.500 -0.1772 0.02795 0.02068 -0.0907 0.9139 0.0363
-5.250 -0.1520 0.02671 0.01922 -0.0907 0.9041 0.0390
-5.000 -0.1234 0.02451 0.01647 -0.0911 0.8970 0.0414
-4.750 -0.0976 0.02322 0.01494 -0.0909 0.8876 0.0445
-4.500 -0.0700 0.02228 0.01382 -0.0909 0.8798 0.0481
-4.250 -0.0431 0.02110 0.01233 -0.0904 0.8711 0.0515
-4.000 -0.0167 0.02027 0.01146 -0.0902 0.8629 0.0560
-3.750 0.0101 0.01949 0.01053 -0.0897 0.8546 0.0612
-3.500 0.0361 0.01874 0.00973 -0.0892 0.8459 0.0670
-3.250 0.0630 0.01819 0.00905 -0.0887 0.8379 0.0760
-3.000 0.0886 0.01763 0.00851 -0.0882 0.8288 0.0861
-2.750 0.1154 0.01714 0.00799 -0.0877 0.8211 0.1000
-2.500 0.1412 0.01675 0.00759 -0.0872 0.8115 0.1174
-2.250 0.1679 0.01629 0.00716 -0.0867 0.8042 0.1397
-2.000 0.1937 0.01591 0.00687 -0.0863 0.7942 0.1705
-1.750 0.2201 0.01546 0.00658 -0.0859 0.7860 0.2220
-1.500 0.2460 0.01501 0.00639 -0.0855 0.7768 0.3071
-1.250 0.2711 0.01454 0.00629 -0.0848 0.7677 0.4267
-1.000 0.2954 0.01406 0.00621 -0.0837 0.7593 0.5640
-0.750 0.3163 0.01360 0.00619 -0.0816 0.7495 0.7110
-0.500 0.3572 0.01298 0.00586 -0.0827 0.7416 1.0000
-0.250 0.3837 0.01307 0.00576 -0.0823 0.7308 1.0000
0.000 0.4104 0.01315 0.00565 -0.0819 0.7209 1.0000
0.250 0.4374 0.01320 0.00552 -0.0814 0.7117 1.0000
0.500 0.4640 0.01331 0.00550 -0.0811 0.7004 1.0000
0.750 0.4908 0.01341 0.00546 -0.0807 0.6901 1.0000
1.000 0.5178 0.01349 0.00538 -0.0802 0.6804 1.0000
1.250 0.5443 0.01362 0.00542 -0.0798 0.6686 1.0000
1.500 0.5710 0.01374 0.00544 -0.0794 0.6573 1.0000
1.750 0.5978 0.01385 0.00544 -0.0790 0.6464 1.0000
2.000 0.6245 0.01397 0.00547 -0.0786 0.6351 1.0000
2.250 0.6509 0.01413 0.00556 -0.0782 0.6226 1.0000
2.500 0.6774 0.01428 0.00565 -0.0778 0.6102 1.0000
2.750 0.7039 0.01444 0.00573 -0.0773 0.5982 1.0000
3.000 0.7303 0.01461 0.00583 -0.0769 0.5860 1.0000
3.250 0.7566 0.01479 0.00595 -0.0764 0.5734 1.0000
3.500 0.7826 0.01499 0.00611 -0.0760 0.5598 1.0000
3.750 0.8086 0.01520 0.00629 -0.0756 0.5463 1.0000
4.000 0.8344 0.01543 0.00650 -0.0751 0.5326 1.0000
4.250 0.8601 0.01567 0.00671 -0.0747 0.5187 1.0000
4.500 0.8856 0.01592 0.00693 -0.0742 0.5047 1.0000
4.750 0.9109 0.01620 0.00719 -0.0737 0.4905 1.0000
5.000 0.9361 0.01649 0.00746 -0.0731 0.4761 1.0000
5.250 0.9609 0.01680 0.00775 -0.0726 0.4616 1.0000
5.500 0.9855 0.01713 0.00809 -0.0720 0.4469 1.0000
5.750 1.0099 0.01749 0.00843 -0.0715 0.4322 1.0000
6.000 1.0339 0.01786 0.00880 -0.0708 0.4172 1.0000
6.250 1.0577 0.01826 0.00922 -0.0702 0.4023 1.0000
6.500 1.0810 0.01869 0.00965 -0.0695 0.3873 1.0000
6.750 1.1040 0.01914 0.01011 -0.0688 0.3722 1.0000
7.000 1.1266 0.01961 0.01060 -0.0681 0.3571 1.0000
7.250 1.1486 0.02012 0.01113 -0.0673 0.3421 1.0000
7.500 1.1702 0.02065 0.01169 -0.0664 0.3269 1.0000
7.750 1.1911 0.02121 0.01227 -0.0656 0.3119 1.0000
8.000 1.2115 0.02181 0.01290 -0.0646 0.2969 1.0000
8.250 1.2311 0.02244 0.01358 -0.0636 0.2820 1.0000
8.500 1.2499 0.02311 0.01428 -0.0625 0.2671 1.0000
8.750 1.2678 0.02382 0.01503 -0.0613 0.2522 1.0000
9.000 1.2847 0.02458 0.01582 -0.0600 0.2376 1.0000
9.250 1.3004 0.02539 0.01668 -0.0586 0.2230 1.0000
9.500 1.3148 0.02625 0.01758 -0.0571 0.2088 1.0000
9.750 1.3277 0.02717 0.01855 -0.0555 0.1948 1.0000
10.000 1.3381 0.02816 0.01957 -0.0536 0.1817 1.0000
10.250 1.3460 0.02924 0.02068 -0.0514 0.1692 1.0000
10.500 1.3536 0.03041 0.02193 -0.0494 0.1569 1.0000
10.750 1.3600 0.03172 0.02331 -0.0475 0.1452 1.0000
11.000 1.3653 0.03319 0.02484 -0.0457 0.1344 1.0000
11.250 1.3688 0.03487 0.02655 -0.0441 0.1244 1.0000
11.500 1.3705 0.03677 0.02847 -0.0426 0.1153 1.0000
11.750 1.3739 0.03869 0.03050 -0.0413 0.1065 1.0000
12.000 1.3743 0.04093 0.03280 -0.0402 0.0992 1.0000
12.250 1.3744 0.04331 0.03527 -0.0393 0.0923 1.0000
12.500 1.3737 0.04591 0.03794 -0.0386 0.0865 1.0000
12.750 1.3726 0.04865 0.04079 -0.0381 0.0811 1.0000
13.000 1.3688 0.05178 0.04396 -0.0378 0.0770 1.0000
13.250 1.3681 0.05472 0.04707 -0.0377 0.0723 1.0000
13.500 1.3639 0.05815 0.05059 -0.0379 0.0688 1.0000
13.750 1.3589 0.06176 0.05425 -0.0382 0.0659 1.0000
14.000 1.3567 0.06522 0.05790 -0.0386 0.0624 1.0000
14.250 1.3524 0.06905 0.06186 -0.0393 0.0595 1.0000
14.500 1.3462 0.07322 0.06612 -0.0404 0.0572 1.0000
14.750 1.3422 0.07722 0.07022 -0.0413 0.0549 1.0000
15.000 1.3384 0.08139 0.07459 -0.0424 0.0525 1.0000
15.250 1.3335 0.08581 0.07915 -0.0438 0.0504 1.0000
15.500 1.3280 0.09038 0.08382 -0.0455 0.0486 1.0000
15.750 1.3236 0.09472 0.08818 -0.0469 0.0469 1.0000
16.000 1.3183 0.09960 0.09328 -0.0488 0.0453 1.0000
16.250 1.3121 0.10475 0.09863 -0.0509 0.0437 1.0000
16.500 1.3055 0.11002 0.10408 -0.0532 0.0423 1.0000
16.750 1.2990 0.11536 0.10954 -0.0558 0.0409 1.0000
17.000 1.2943 0.12037 0.11464 -0.0582 0.0397 1.0000
17.250 1.2936 0.12434 0.11862 -0.0599 0.0383 1.0000
17.500 1.2824 0.13117 0.12567 -0.0637 0.0376 1.0000
17.750 1.2693 0.13861 0.13334 -0.0680 0.0369 1.0000
18.000 1.2542 0.14682 0.14177 -0.0730 0.0364 1.0000
18.250 1.2348 0.15651 0.15167 -0.0791 0.0360 1.0000
18.500 1.2043 0.16993 0.16529 -0.0879 0.0360 1.0000
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Polar data table (+)
Polar graphs
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