S2091-101-83 (s2091-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 50,000 Max Cl/Cd: 38.19 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2091-il-50000-n5.txt Download as CSV file: xf-s2091-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3383 0.11811 0.11114 -0.0259 1.0000 0.1029
-9.500 -0.3444 0.11634 0.10948 -0.0290 1.0000 0.1041
-9.250 -0.3485 0.11402 0.10726 -0.0318 1.0000 0.1045
-9.000 -0.3226 0.10796 0.10117 -0.0290 1.0000 0.1077
-8.750 -0.3167 0.10472 0.09798 -0.0297 1.0000 0.1088
-8.500 -0.3146 0.10159 0.09494 -0.0310 1.0000 0.1085
-8.250 -0.3303 0.09451 0.08791 -0.0380 1.0000 0.0631
-8.000 -0.3205 0.09134 0.08479 -0.0368 1.0000 0.0614
-7.750 -0.3213 0.08840 0.08196 -0.0367 1.0000 0.0601
-7.500 -0.3279 0.08584 0.07954 -0.0363 1.0000 0.0589
-7.250 -0.3375 0.08339 0.07723 -0.0359 1.0000 0.0578
-7.000 -0.3491 0.08082 0.07479 -0.0357 1.0000 0.0568
-6.750 -0.3613 0.07818 0.07225 -0.0356 1.0000 0.0560
-6.500 -0.3723 0.07503 0.06916 -0.0362 1.0000 0.0551
-6.250 -0.3803 0.07118 0.06532 -0.0378 1.0000 0.0543
-6.000 -0.3612 0.06626 0.06030 -0.0437 0.9925 0.0553
-5.750 -0.3334 0.06050 0.05433 -0.0514 0.9829 0.0568
-5.500 -0.3048 0.05423 0.04771 -0.0590 0.9734 0.0574
-5.250 -0.2753 0.04828 0.04128 -0.0653 0.9642 0.0577
-5.000 -0.2405 0.04308 0.03542 -0.0710 0.9567 0.0605
-4.750 -0.2074 0.03845 0.02984 -0.0749 0.9481 0.0635
-4.500 -0.1734 0.03579 0.02694 -0.0775 0.9413 0.0661
-4.250 -0.1406 0.03384 0.02463 -0.0794 0.9330 0.0716
-4.000 -0.1022 0.03128 0.02132 -0.0818 0.9266 0.0766
-3.750 -0.0704 0.02992 0.01988 -0.0831 0.9182 0.0829
-3.500 -0.0332 0.02838 0.01791 -0.0847 0.9115 0.0914
-3.250 -0.0024 0.02738 0.01677 -0.0853 0.9026 0.1018
-3.000 0.0312 0.02640 0.01568 -0.0863 0.8949 0.1150
-2.750 0.0630 0.02561 0.01475 -0.0869 0.8862 0.1325
-2.500 0.0938 0.02491 0.01402 -0.0874 0.8774 0.1539
-2.250 0.1268 0.02420 0.01333 -0.0882 0.8693 0.1846
-2.000 0.1548 0.02360 0.01285 -0.0883 0.8594 0.2279
-1.750 0.1877 0.02273 0.01241 -0.0892 0.8521 0.3161
-1.500 0.2097 0.02202 0.01236 -0.0881 0.8413 0.4678
-1.250 0.2300 0.02122 0.01231 -0.0853 0.8328 0.6770
-1.000 0.2747 0.02058 0.01189 -0.0870 0.8241 1.0000
-0.750 0.3024 0.02076 0.01172 -0.0869 0.8137 1.0000
-0.500 0.3340 0.02083 0.01148 -0.0872 0.8052 1.0000
-0.250 0.3588 0.02107 0.01148 -0.0867 0.7935 1.0000
0.000 0.3859 0.02125 0.01144 -0.0864 0.7831 1.0000
0.250 0.4158 0.02133 0.01130 -0.0863 0.7742 1.0000
0.500 0.4403 0.02159 0.01139 -0.0856 0.7623 1.0000
0.750 0.4668 0.02178 0.01142 -0.0851 0.7515 1.0000
1.000 0.4963 0.02182 0.01131 -0.0848 0.7426 1.0000
1.250 0.5206 0.02209 0.01147 -0.0841 0.7303 1.0000
1.500 0.5461 0.02231 0.01159 -0.0835 0.7189 1.0000
1.750 0.5740 0.02241 0.01158 -0.0830 0.7089 1.0000
2.000 0.6003 0.02257 0.01166 -0.0823 0.6976 1.0000
2.250 0.6249 0.02283 0.01187 -0.0816 0.6853 1.0000
2.500 0.6506 0.02303 0.01202 -0.0809 0.6735 1.0000
2.750 0.6781 0.02312 0.01204 -0.0803 0.6629 1.0000
3.000 0.7041 0.02329 0.01217 -0.0796 0.6510 1.0000
3.250 0.7286 0.02356 0.01243 -0.0788 0.6379 1.0000
3.500 0.7536 0.02380 0.01267 -0.0780 0.6252 1.0000
3.750 0.7791 0.02401 0.01286 -0.0773 0.6126 1.0000
4.000 0.8053 0.02417 0.01302 -0.0765 0.6005 1.0000
4.250 0.8320 0.02430 0.01313 -0.0758 0.5884 1.0000
4.500 0.8560 0.02461 0.01346 -0.0750 0.5744 1.0000
4.750 0.8802 0.02493 0.01381 -0.0742 0.5604 1.0000
5.000 0.9044 0.02525 0.01418 -0.0733 0.5464 1.0000
5.250 0.9285 0.02558 0.01455 -0.0725 0.5323 1.0000
5.500 0.9525 0.02592 0.01493 -0.0716 0.5181 1.0000
5.750 0.9763 0.02629 0.01535 -0.0708 0.5037 1.0000
6.000 0.9999 0.02668 0.01579 -0.0699 0.4892 1.0000
6.250 1.0232 0.02710 0.01625 -0.0690 0.4746 1.0000
6.500 1.0461 0.02755 0.01678 -0.0680 0.4599 1.0000
6.750 1.0686 0.02804 0.01732 -0.0671 0.4451 1.0000
7.000 1.0907 0.02856 0.01791 -0.0661 0.4302 1.0000
7.250 1.1122 0.02913 0.01854 -0.0651 0.4153 1.0000
7.500 1.1332 0.02974 0.01924 -0.0640 0.4002 1.0000
7.750 1.1535 0.03039 0.01997 -0.0629 0.3852 1.0000
8.000 1.1731 0.03109 0.02075 -0.0618 0.3702 1.0000
8.250 1.1918 0.03184 0.02157 -0.0606 0.3551 1.0000
8.500 1.2097 0.03263 0.02247 -0.0593 0.3401 1.0000
8.750 1.2264 0.03348 0.02341 -0.0579 0.3251 1.0000
9.000 1.2420 0.03439 0.02440 -0.0565 0.3102 1.0000
9.250 1.2562 0.03536 0.02546 -0.0549 0.2953 1.0000
9.500 1.2689 0.03640 0.02661 -0.0533 0.2807 1.0000
9.750 1.2800 0.03752 0.02781 -0.0515 0.2664 1.0000
10.000 1.2892 0.03872 0.02908 -0.0497 0.2525 1.0000
10.250 1.2958 0.03998 0.03038 -0.0476 0.2393 1.0000
10.500 1.3001 0.04142 0.03191 -0.0455 0.2266 1.0000
10.750 1.3017 0.04316 0.03377 -0.0435 0.2141 1.0000
11.000 1.3030 0.04506 0.03581 -0.0418 0.2022 1.0000
11.250 1.3037 0.04709 0.03792 -0.0403 0.1909 1.0000
11.500 1.3049 0.04917 0.04004 -0.0390 0.1803 1.0000
11.750 1.3046 0.05152 0.04246 -0.0379 0.1700 1.0000
12.000 1.3014 0.05437 0.04547 -0.0372 0.1601 1.0000
12.250 1.3006 0.05709 0.04825 -0.0366 0.1514 1.0000
12.500 1.2989 0.05995 0.05118 -0.0362 0.1428 1.0000
12.750 1.2940 0.06350 0.05491 -0.0361 0.1351 1.0000
13.000 1.2952 0.06616 0.05754 -0.0359 0.1279 1.0000
13.250 1.2864 0.07062 0.06229 -0.0365 0.1217 1.0000
13.500 1.2869 0.07356 0.06520 -0.0365 0.1154 1.0000
13.750 1.2760 0.07862 0.07053 -0.0378 0.1104 1.0000
14.000 1.2695 0.08300 0.07506 -0.0388 0.1055 1.0000
14.250 1.2685 0.08654 0.07861 -0.0394 0.1009 1.0000
14.500 1.2508 0.09335 0.08575 -0.0420 0.0978 1.0000
14.750 1.2356 0.09994 0.09255 -0.0448 0.0948 1.0000
15.000 1.2474 0.10112 0.09359 -0.0442 0.0896 1.0000
15.250 1.2207 0.11053 0.10332 -0.0490 0.0884 1.0000
15.500 1.1858 0.12252 0.11558 -0.0558 0.0878 1.0000
15.750 1.1318 0.14082 0.13399 -0.0668 0.0879 1.0000
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Polar data table (+)
Polar graphs
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