S2091-101-83 (s2091-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 100,000 Max Cl/Cd: 54.74 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2091-il-100000.txt Download as CSV file: xf-s2091-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3108 0.10138 0.09661 -0.0298 1.0000 0.0903
-8.500 -0.3184 0.09966 0.09500 -0.0335 1.0000 0.0924
-8.250 -0.3386 0.09889 0.09441 -0.0379 1.0000 0.0932
-8.000 -0.3065 0.09232 0.08779 -0.0335 1.0000 0.0967
-7.750 -0.3004 0.08967 0.08520 -0.0329 1.0000 0.0995
-7.500 -0.3045 0.08764 0.08327 -0.0325 1.0000 0.1026
-7.250 -0.3230 0.08676 0.08254 -0.0301 1.0000 0.1044
-7.000 -0.3496 0.08663 0.08256 -0.0260 1.0000 0.1050
-6.750 -0.3734 0.08602 0.08206 -0.0241 1.0000 0.1060
-6.500 -0.4002 0.08503 0.08114 -0.0281 1.0000 0.1074
-6.250 -0.4134 0.08184 0.07794 -0.0323 1.0000 0.1085
-6.000 -0.3981 0.07848 0.07469 -0.0260 0.9977 0.1106
-5.750 -0.3693 0.07467 0.07085 -0.0292 0.9915 0.1168
-5.500 -0.3349 0.06796 0.06401 -0.0431 0.9827 0.1259
-5.250 -0.2993 0.06255 0.05834 -0.0547 0.9734 0.1396
-5.000 -0.2746 0.06010 0.05599 -0.0534 0.9670 0.1490
-4.750 -0.2405 0.05576 0.05153 -0.0596 0.9597 0.1622
-4.500 -0.1859 0.04028 0.03447 -0.0769 0.9510 0.0923
-4.250 -0.1470 0.03530 0.02913 -0.0809 0.9454 0.0875
-4.000 -0.1114 0.03135 0.02451 -0.0834 0.9379 0.0858
-3.750 -0.0700 0.02842 0.02094 -0.0862 0.9316 0.0878
-3.500 -0.0294 0.02655 0.01840 -0.0883 0.9249 0.0928
-3.250 0.0082 0.02472 0.01645 -0.0903 0.9176 0.1000
-3.000 0.0565 0.02311 0.01457 -0.0937 0.9135 0.1118
-2.750 0.0850 0.02229 0.01368 -0.0937 0.9031 0.1260
-2.500 0.1289 0.02121 0.01262 -0.0962 0.8981 0.1507
-2.250 0.1548 0.02056 0.01210 -0.0958 0.8872 0.1759
-2.000 0.1883 0.01980 0.01150 -0.0965 0.8795 0.2178
-1.750 0.2178 0.01888 0.01106 -0.0966 0.8704 0.2989
-1.500 0.2394 0.01761 0.01104 -0.0950 0.8611 0.5755
-1.250 0.2895 0.01636 0.01058 -0.0965 0.8553 1.0000
-1.000 0.3167 0.01649 0.01043 -0.0962 0.8448 1.0000
-0.750 0.3483 0.01644 0.01011 -0.0962 0.8368 1.0000
-0.500 0.3724 0.01663 0.01010 -0.0953 0.8249 1.0000
-0.250 0.3989 0.01673 0.01002 -0.0946 0.8146 1.0000
0.000 0.4277 0.01668 0.00979 -0.0940 0.8060 1.0000
0.250 0.4521 0.01685 0.00983 -0.0931 0.7940 1.0000
0.500 0.4783 0.01693 0.00978 -0.0923 0.7837 1.0000
0.750 0.5063 0.01686 0.00956 -0.0915 0.7748 1.0000
1.000 0.5311 0.01702 0.00963 -0.0906 0.7626 1.0000
1.250 0.5569 0.01711 0.00963 -0.0898 0.7515 1.0000
1.500 0.5853 0.01698 0.00937 -0.0889 0.7430 1.0000
1.750 0.6102 0.01713 0.00946 -0.0881 0.7302 1.0000
2.000 0.6358 0.01724 0.00951 -0.0872 0.7181 1.0000
2.250 0.6623 0.01728 0.00947 -0.0864 0.7070 1.0000
2.500 0.6902 0.01720 0.00929 -0.0856 0.6970 1.0000
2.750 0.7156 0.01734 0.00939 -0.0848 0.6838 1.0000
3.000 0.7414 0.01746 0.00947 -0.0840 0.6708 1.0000
3.250 0.7675 0.01755 0.00954 -0.0833 0.6581 1.0000
3.500 0.7941 0.01762 0.00955 -0.0825 0.6456 1.0000
3.750 0.8212 0.01766 0.00951 -0.0818 0.6334 1.0000
4.000 0.8479 0.01773 0.00953 -0.0810 0.6203 1.0000
4.250 0.8737 0.01788 0.00967 -0.0803 0.6059 1.0000
4.500 0.8995 0.01805 0.00981 -0.0796 0.5914 1.0000
4.750 0.9252 0.01823 0.00997 -0.0789 0.5766 1.0000
5.000 0.9509 0.01843 0.01016 -0.0782 0.5616 1.0000
5.250 0.9765 0.01865 0.01036 -0.0775 0.5464 1.0000
5.500 1.0020 0.01889 0.01057 -0.0768 0.5309 1.0000
5.750 1.0273 0.01916 0.01083 -0.0760 0.5152 1.0000
6.000 1.0525 0.01945 0.01109 -0.0753 0.4993 1.0000
6.250 1.0775 0.01977 0.01137 -0.0746 0.4833 1.0000
6.500 1.1020 0.02014 0.01173 -0.0739 0.4670 1.0000
6.750 1.1254 0.02056 0.01219 -0.0730 0.4498 1.0000
7.000 1.1487 0.02100 0.01266 -0.0722 0.4327 1.0000
7.250 1.1717 0.02146 0.01313 -0.0714 0.4156 1.0000
7.500 1.1945 0.02195 0.01364 -0.0705 0.3986 1.0000
7.750 1.2170 0.02245 0.01414 -0.0696 0.3817 1.0000
8.000 1.2390 0.02298 0.01466 -0.0686 0.3648 1.0000
8.250 1.2607 0.02354 0.01522 -0.0677 0.3480 1.0000
8.500 1.2817 0.02416 0.01579 -0.0666 0.3312 1.0000
8.750 1.3003 0.02483 0.01655 -0.0654 0.3136 1.0000
9.000 1.3183 0.02553 0.01731 -0.0640 0.2960 1.0000
9.250 1.3355 0.02626 0.01809 -0.0626 0.2786 1.0000
9.500 1.3518 0.02704 0.01888 -0.0611 0.2613 1.0000
9.750 1.3668 0.02789 0.01971 -0.0596 0.2442 1.0000
10.000 1.3807 0.02887 0.02064 -0.0579 0.2274 1.0000
10.250 1.3906 0.02994 0.02180 -0.0558 0.2102 1.0000
10.500 1.3993 0.03111 0.02303 -0.0536 0.1938 1.0000
10.750 1.4061 0.03239 0.02432 -0.0512 0.1783 1.0000
11.000 1.4104 0.03375 0.02568 -0.0486 0.1645 1.0000
11.250 1.4139 0.03526 0.02719 -0.0461 0.1520 1.0000
11.500 1.4178 0.03689 0.02878 -0.0438 0.1407 1.0000
11.750 1.4229 0.03861 0.03043 -0.0419 0.1301 1.0000
12.000 1.4234 0.04055 0.03258 -0.0397 0.1211 1.0000
12.250 1.4284 0.04261 0.03466 -0.0381 0.1128 1.0000
12.500 1.4343 0.04455 0.03657 -0.0367 0.1052 1.0000
12.750 1.4367 0.04703 0.03925 -0.0352 0.0989 1.0000
13.000 1.4454 0.04904 0.04117 -0.0342 0.0923 1.0000
13.250 1.4459 0.05190 0.04430 -0.0330 0.0877 1.0000
13.500 1.4462 0.05449 0.04705 -0.0319 0.0832 1.0000
13.750 1.4590 0.05711 0.04960 -0.0313 0.0782 1.0000
14.000 1.4507 0.06055 0.05340 -0.0304 0.0758 1.0000
14.250 1.4440 0.06405 0.05718 -0.0298 0.0731 1.0000
14.500 1.4473 0.06681 0.05998 -0.0295 0.0699 1.0000
14.750 1.4494 0.07070 0.06394 -0.0292 0.0670 1.0000
15.000 1.4311 0.07554 0.06913 -0.0296 0.0662 1.0000
15.250 1.4120 0.08094 0.07486 -0.0307 0.0655 1.0000
15.500 1.3901 0.08702 0.08123 -0.0326 0.0650 1.0000
15.750 1.3651 0.09390 0.08840 -0.0354 0.0648 1.0000
16.000 1.3371 0.10179 0.09656 -0.0392 0.0650 1.0000
16.250 1.3054 0.11101 0.10603 -0.0444 0.0655 1.0000
16.500 1.2710 0.12167 0.11689 -0.0509 0.0663 1.0000
16.750 1.2352 0.13373 0.12910 -0.0586 0.0672 1.0000
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Polar data table (+)
Polar graphs
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