S2091-101-83 (s2091-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 500,000 Max Cl/Cd: 99.46 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2091-il-500000-n5.txt Download as CSV file: xf-s2091-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3796 0.11973 0.11735 -0.0174 1.0000 0.0080
-11.000 -0.3752 0.11588 0.11351 -0.0190 1.0000 0.0080
-9.500 -0.5931 0.02815 0.02479 -0.0819 0.9149 0.0082
-9.250 -0.5802 0.02482 0.02099 -0.0824 0.9025 0.0085
-9.000 -0.5623 0.02254 0.01833 -0.0825 0.8925 0.0087
-8.750 -0.5418 0.02080 0.01624 -0.0823 0.8833 0.0089
-8.500 -0.5196 0.01932 0.01452 -0.0822 0.8745 0.0092
-8.250 -0.4958 0.01840 0.01344 -0.0819 0.8666 0.0095
-8.000 -0.4706 0.01763 0.01252 -0.0818 0.8583 0.0098
-7.750 -0.4455 0.01690 0.01164 -0.0816 0.8508 0.0102
-7.500 -0.4197 0.01614 0.01072 -0.0814 0.8427 0.0106
-7.250 -0.3940 0.01542 0.00981 -0.0812 0.8354 0.0111
-7.000 -0.3676 0.01474 0.00896 -0.0810 0.8274 0.0116
-6.750 -0.3414 0.01413 0.00823 -0.0808 0.8201 0.0122
-6.500 -0.3142 0.01376 0.00780 -0.0807 0.8122 0.0130
-6.000 -0.2599 0.01295 0.00674 -0.0804 0.7971 0.0149
-5.750 -0.2330 0.01246 0.00617 -0.0803 0.7895 0.0158
-5.500 -0.2054 0.01210 0.00574 -0.0802 0.7818 0.0169
-5.250 -0.1779 0.01177 0.00530 -0.0800 0.7741 0.0181
-5.000 -0.1502 0.01140 0.00485 -0.0799 0.7662 0.0193
-4.750 -0.1226 0.01113 0.00453 -0.0798 0.7585 0.0209
-4.500 -0.0946 0.01088 0.00420 -0.0798 0.7504 0.0225
-4.000 -0.0388 0.01034 0.00356 -0.0796 0.7343 0.0263
-3.750 -0.0109 0.01016 0.00328 -0.0795 0.7264 0.0283
-3.500 0.0172 0.00990 0.00302 -0.0795 0.7179 0.0314
-3.250 0.0453 0.00974 0.00279 -0.0794 0.7098 0.0347
-3.000 0.0735 0.00954 0.00259 -0.0793 0.7010 0.0400
-2.750 0.1016 0.00939 0.00241 -0.0793 0.6927 0.0472
-2.500 0.1298 0.00926 0.00226 -0.0792 0.6834 0.0554
-2.250 0.1581 0.00916 0.00212 -0.0792 0.6745 0.0632
-1.750 0.2145 0.00894 0.00189 -0.0791 0.6554 0.0843
-1.500 0.2426 0.00884 0.00180 -0.0791 0.6460 0.0996
-1.250 0.2707 0.00872 0.00172 -0.0790 0.6360 0.1246
-1.000 0.2987 0.00858 0.00165 -0.0791 0.6258 0.1606
-0.750 0.3267 0.00845 0.00160 -0.0791 0.6157 0.2028
-0.500 0.3546 0.00832 0.00156 -0.0791 0.6050 0.2518
-0.250 0.3825 0.00816 0.00155 -0.0791 0.5941 0.3164
0.000 0.4102 0.00802 0.00155 -0.0791 0.5833 0.3848
0.250 0.4378 0.00791 0.00156 -0.0790 0.5719 0.4507
0.500 0.4652 0.00776 0.00159 -0.0790 0.5602 0.5316
0.750 0.4919 0.00755 0.00165 -0.0787 0.5489 0.6331
1.000 0.5164 0.00727 0.00173 -0.0779 0.5376 0.7622
1.250 0.5393 0.00694 0.00176 -0.0763 0.5263 0.9342
1.500 0.5751 0.00702 0.00177 -0.0779 0.5130 1.0000
1.750 0.6028 0.00714 0.00181 -0.0778 0.5007 1.0000
2.000 0.6305 0.00728 0.00187 -0.0777 0.4880 1.0000
2.250 0.6580 0.00743 0.00194 -0.0776 0.4754 1.0000
2.500 0.6855 0.00758 0.00201 -0.0775 0.4624 1.0000
2.750 0.7129 0.00775 0.00210 -0.0774 0.4493 1.0000
3.250 0.7674 0.00809 0.00232 -0.0772 0.4225 1.0000
3.500 0.7946 0.00827 0.00244 -0.0770 0.4093 1.0000
3.750 0.8217 0.00847 0.00258 -0.0769 0.3958 1.0000
4.000 0.8486 0.00867 0.00272 -0.0768 0.3824 1.0000
4.250 0.8754 0.00889 0.00287 -0.0766 0.3690 1.0000
4.500 0.9020 0.00911 0.00305 -0.0764 0.3553 1.0000
4.750 0.9285 0.00935 0.00323 -0.0762 0.3418 1.0000
5.000 0.9548 0.00960 0.00343 -0.0760 0.3276 1.0000
5.250 0.9809 0.00987 0.00364 -0.0758 0.3139 1.0000
5.500 1.0069 0.01014 0.00386 -0.0756 0.3002 1.0000
5.750 1.0327 0.01043 0.00410 -0.0753 0.2858 1.0000
6.000 1.0583 0.01072 0.00435 -0.0750 0.2720 1.0000
6.250 1.0838 0.01102 0.00462 -0.0747 0.2585 1.0000
6.500 1.1089 0.01135 0.00490 -0.0744 0.2447 1.0000
6.750 1.1338 0.01169 0.00520 -0.0741 0.2310 1.0000
7.000 1.1584 0.01205 0.00552 -0.0737 0.2170 1.0000
7.250 1.1825 0.01245 0.00586 -0.0732 0.2023 1.0000
7.500 1.2064 0.01285 0.00622 -0.0728 0.1885 1.0000
7.750 1.2300 0.01326 0.00659 -0.0723 0.1757 1.0000
8.000 1.2533 0.01368 0.00699 -0.0717 0.1636 1.0000
8.250 1.2760 0.01415 0.00741 -0.0711 0.1507 1.0000
8.500 1.2981 0.01464 0.00786 -0.0704 0.1376 1.0000
8.750 1.3195 0.01518 0.00836 -0.0697 0.1241 1.0000
9.000 1.3402 0.01574 0.00888 -0.0688 0.1113 1.0000
9.250 1.3601 0.01634 0.00944 -0.0679 0.0991 1.0000
9.500 1.3793 0.01697 0.01003 -0.0668 0.0880 1.0000
9.750 1.3973 0.01764 0.01067 -0.0656 0.0774 1.0000
10.000 1.4147 0.01831 0.01131 -0.0644 0.0684 1.0000
10.250 1.4312 0.01898 0.01199 -0.0630 0.0607 1.0000
10.500 1.4454 0.01970 0.01270 -0.0612 0.0543 1.0000
10.750 1.4571 0.02042 0.01344 -0.0591 0.0490 1.0000
11.000 1.4684 0.02118 0.01424 -0.0570 0.0450 1.0000
11.250 1.4793 0.02200 0.01509 -0.0551 0.0414 1.0000
11.500 1.4886 0.02298 0.01609 -0.0531 0.0381 1.0000
11.750 1.4995 0.02389 0.01707 -0.0515 0.0355 1.0000
12.000 1.5081 0.02502 0.01824 -0.0498 0.0327 1.0000
12.250 1.5163 0.02623 0.01950 -0.0482 0.0304 1.0000
12.500 1.5254 0.02744 0.02079 -0.0468 0.0286 1.0000
12.750 1.5324 0.02886 0.02227 -0.0455 0.0267 1.0000
13.000 1.5377 0.03050 0.02397 -0.0442 0.0251 1.0000
13.250 1.5449 0.03204 0.02560 -0.0432 0.0239 1.0000
13.500 1.5508 0.03376 0.02740 -0.0422 0.0226 1.0000
13.750 1.5547 0.03574 0.02945 -0.0414 0.0213 1.0000
14.000 1.5564 0.03801 0.03180 -0.0406 0.0201 1.0000
14.250 1.5597 0.04022 0.03410 -0.0401 0.0192 1.0000
14.500 1.5622 0.04260 0.03659 -0.0398 0.0184 1.0000
14.750 1.5631 0.04523 0.03932 -0.0396 0.0176 1.0000
15.000 1.5621 0.04817 0.04235 -0.0396 0.0168 1.0000
15.250 1.5590 0.05149 0.04575 -0.0398 0.0161 1.0000
15.500 1.5566 0.05486 0.04923 -0.0402 0.0155 1.0000
15.750 1.5547 0.05830 0.05279 -0.0408 0.0149 1.0000
16.000 1.5516 0.06201 0.05662 -0.0416 0.0143 1.0000
16.250 1.5471 0.06607 0.06079 -0.0427 0.0138 1.0000
16.500 1.5409 0.07049 0.06532 -0.0440 0.0134 1.0000
16.750 1.5333 0.07528 0.07022 -0.0456 0.0130 1.0000
17.000 1.5236 0.08055 0.07560 -0.0476 0.0126 1.0000
17.250 1.5131 0.08610 0.08128 -0.0497 0.0123 1.0000
17.500 1.5057 0.09130 0.08661 -0.0519 0.0120 1.0000
17.750 1.4965 0.09686 0.09231 -0.0542 0.0117 1.0000
18.000 1.4870 0.10258 0.09816 -0.0568 0.0114 1.0000
18.250 1.4768 0.10856 0.10427 -0.0595 0.0112 1.0000
18.500 1.4667 0.11462 0.11045 -0.0625 0.0109 1.0000
18.750 1.4556 0.12093 0.11688 -0.0656 0.0107 1.0000
19.000 1.4447 0.12730 0.12336 -0.0689 0.0105 1.0000
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Polar data table (+)
Polar graphs
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