S2091-101-83 (s2091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.23 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2091-il-1000000.txt Download as CSV file: xf-s2091-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2633 0.09406 0.09259 -0.0292 0.9753 0.0134
-9.750 -0.2531 0.08976 0.08827 -0.0322 0.9593 0.0138
-9.500 -0.5949 0.02709 0.02447 -0.0822 0.9308 0.0091
-9.250 -0.5832 0.02383 0.02079 -0.0824 0.9171 0.0093
-9.000 -0.5659 0.02151 0.01812 -0.0824 0.9066 0.0094
-8.750 -0.5449 0.02002 0.01635 -0.0821 0.8975 0.0095
-8.500 -0.5216 0.01879 0.01490 -0.0819 0.8886 0.0097
-8.250 -0.5025 0.01618 0.01188 -0.0818 0.8801 0.0101
-8.000 -0.4771 0.01545 0.01105 -0.0816 0.8719 0.0104
-7.750 -0.4509 0.01502 0.01053 -0.0814 0.8645 0.0108
-7.500 -0.4244 0.01450 0.00992 -0.0813 0.8566 0.0113
-7.250 -0.3979 0.01397 0.00926 -0.0811 0.8493 0.0118
-7.000 -0.3711 0.01340 0.00856 -0.0809 0.8415 0.0122
-6.750 -0.3440 0.01299 0.00801 -0.0807 0.8343 0.0125
-6.500 -0.3183 0.01185 0.00673 -0.0806 0.8265 0.0133
-6.250 -0.2910 0.01151 0.00632 -0.0805 0.8193 0.0139
-6.000 -0.2633 0.01114 0.00589 -0.0804 0.8116 0.0146
-5.750 -0.2356 0.01085 0.00549 -0.0802 0.8043 0.0154
-5.500 -0.2081 0.01027 0.00483 -0.0801 0.7966 0.0164
-5.000 -0.1523 0.00974 0.00420 -0.0800 0.7815 0.0188
-4.500 -0.0963 0.00910 0.00344 -0.0799 0.7664 0.0217
-4.250 -0.0682 0.00891 0.00319 -0.0798 0.7588 0.0233
-4.000 -0.0398 0.00867 0.00290 -0.0797 0.7509 0.0248
-3.500 0.0168 0.00827 0.00243 -0.0797 0.7350 0.0296
-3.250 0.0450 0.00804 0.00216 -0.0796 0.7270 0.0334
-3.000 0.0736 0.00787 0.00198 -0.0796 0.7185 0.0381
-2.750 0.1019 0.00773 0.00182 -0.0796 0.7103 0.0460
-2.500 0.1304 0.00758 0.00169 -0.0796 0.7015 0.0568
-2.250 0.1588 0.00749 0.00159 -0.0796 0.6930 0.0662
-2.000 0.1873 0.00737 0.00148 -0.0796 0.6839 0.0775
-1.750 0.2158 0.00727 0.00139 -0.0796 0.6751 0.0908
-1.500 0.2441 0.00718 0.00131 -0.0796 0.6658 0.1094
-1.250 0.2726 0.00705 0.00124 -0.0796 0.6563 0.1377
-1.000 0.3009 0.00689 0.00119 -0.0797 0.6468 0.1809
-0.750 0.3289 0.00668 0.00115 -0.0797 0.6366 0.2544
-0.500 0.3570 0.00646 0.00114 -0.0798 0.6266 0.3332
-0.250 0.3849 0.00627 0.00114 -0.0799 0.6165 0.4186
0.000 0.4128 0.00611 0.00115 -0.0799 0.6059 0.5013
0.250 0.4406 0.00595 0.00117 -0.0799 0.5953 0.5815
0.500 0.4678 0.00575 0.00121 -0.0797 0.5848 0.6798
0.750 0.4933 0.00552 0.00127 -0.0791 0.5739 0.7954
1.000 0.5183 0.00519 0.00129 -0.0779 0.5628 0.9619
1.250 0.5524 0.00526 0.00129 -0.0792 0.5508 1.0000
1.500 0.5805 0.00537 0.00132 -0.0792 0.5390 1.0000
1.750 0.6085 0.00548 0.00136 -0.0791 0.5269 1.0000
2.000 0.6365 0.00560 0.00141 -0.0791 0.5141 1.0000
2.250 0.6646 0.00571 0.00146 -0.0791 0.5015 1.0000
2.500 0.6925 0.00583 0.00152 -0.0790 0.4887 1.0000
2.750 0.7204 0.00597 0.00159 -0.0790 0.4761 1.0000
3.000 0.7481 0.00611 0.00167 -0.0789 0.4628 1.0000
3.250 0.7758 0.00626 0.00176 -0.0789 0.4496 1.0000
3.500 0.8034 0.00643 0.00186 -0.0788 0.4357 1.0000
4.000 0.8583 0.00676 0.00208 -0.0787 0.4079 1.0000
4.250 0.8856 0.00694 0.00220 -0.0786 0.3937 1.0000
4.500 0.9128 0.00713 0.00233 -0.0785 0.3792 1.0000
4.750 0.9399 0.00733 0.00248 -0.0784 0.3648 1.0000
5.000 0.9668 0.00754 0.00263 -0.0783 0.3498 1.0000
5.250 0.9936 0.00777 0.00279 -0.0781 0.3347 1.0000
5.500 1.0202 0.00800 0.00298 -0.0780 0.3199 1.0000
5.750 1.0466 0.00825 0.00316 -0.0778 0.3050 1.0000
6.000 1.0729 0.00850 0.00336 -0.0776 0.2903 1.0000
6.250 1.0990 0.00877 0.00358 -0.0774 0.2755 1.0000
6.500 1.1248 0.00907 0.00380 -0.0772 0.2598 1.0000
6.750 1.1505 0.00936 0.00404 -0.0769 0.2454 1.0000
7.000 1.1761 0.00966 0.00429 -0.0767 0.2317 1.0000
7.250 1.2015 0.00996 0.00455 -0.0764 0.2186 1.0000
7.500 1.2266 0.01029 0.00483 -0.0761 0.2052 1.0000
7.750 1.2514 0.01063 0.00512 -0.0757 0.1920 1.0000
8.000 1.2758 0.01100 0.00544 -0.0753 0.1782 1.0000
8.250 1.2998 0.01138 0.00577 -0.0748 0.1646 1.0000
8.500 1.3234 0.01181 0.00613 -0.0743 0.1505 1.0000
8.750 1.3464 0.01226 0.00652 -0.0738 0.1364 1.0000
9.000 1.3686 0.01276 0.00695 -0.0731 0.1214 1.0000
9.250 1.3902 0.01329 0.00741 -0.0724 0.1074 1.0000
9.500 1.4111 0.01386 0.00791 -0.0715 0.0937 1.0000
9.750 1.4316 0.01443 0.00843 -0.0706 0.0820 1.0000
10.000 1.4516 0.01501 0.00896 -0.0696 0.0718 1.0000
10.250 1.4710 0.01559 0.00952 -0.0686 0.0629 1.0000
10.500 1.4893 0.01622 0.01011 -0.0674 0.0550 1.0000
10.750 1.5062 0.01690 0.01075 -0.0660 0.0481 1.0000
11.000 1.5239 0.01746 0.01134 -0.0647 0.0439 1.0000
11.250 1.5372 0.01819 0.01206 -0.0628 0.0387 1.0000
11.500 1.5507 0.01874 0.01264 -0.0608 0.0363 1.0000
11.750 1.5597 0.01951 0.01342 -0.0583 0.0331 1.0000
12.000 1.5701 0.02027 0.01422 -0.0561 0.0305 1.0000
12.250 1.5808 0.02107 0.01506 -0.0542 0.0284 1.0000
12.500 1.5879 0.02215 0.01615 -0.0520 0.0260 1.0000
12.750 1.5978 0.02311 0.01717 -0.0503 0.0243 1.0000
13.000 1.6070 0.02416 0.01827 -0.0487 0.0226 1.0000
13.250 1.6127 0.02554 0.01967 -0.0470 0.0208 1.0000
13.500 1.6192 0.02693 0.02113 -0.0455 0.0195 1.0000
13.750 1.6276 0.02822 0.02250 -0.0443 0.0186 1.0000
14.000 1.6336 0.02978 0.02410 -0.0431 0.0174 1.0000
14.250 1.6357 0.03176 0.02613 -0.0418 0.0163 1.0000
14.500 1.6389 0.03373 0.02819 -0.0409 0.0155 1.0000
14.750 1.6435 0.03566 0.03020 -0.0401 0.0150 1.0000
15.000 1.6477 0.03768 0.03229 -0.0395 0.0143 1.0000
15.250 1.6499 0.03997 0.03466 -0.0390 0.0137 1.0000
15.500 1.6481 0.04282 0.03757 -0.0387 0.0130 1.0000
15.750 1.6403 0.04646 0.04132 -0.0386 0.0124 1.0000
16.000 1.6406 0.04932 0.04428 -0.0387 0.0121 1.0000
16.250 1.6401 0.05240 0.04745 -0.0390 0.0118 1.0000
16.500 1.6384 0.05573 0.05089 -0.0396 0.0114 1.0000
16.750 1.6352 0.05939 0.05466 -0.0403 0.0111 1.0000
17.000 1.6297 0.06353 0.05889 -0.0414 0.0107 1.0000
17.250 1.6234 0.06787 0.06332 -0.0426 0.0104 1.0000
17.500 1.6136 0.07293 0.06849 -0.0443 0.0102 1.0000
17.750 1.6003 0.07870 0.07438 -0.0464 0.0099 1.0000
18.000 1.5848 0.08504 0.08085 -0.0489 0.0097 1.0000
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Polar data table (+)
Polar graphs
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