S2046 (s2046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.27 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2046-il-1000000.txt Download as CSV file: xf-s2046-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S2046
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5977 0.05414 0.05243 -0.0507 1.0000 0.0130
-9.500 -0.6032 0.04861 0.04683 -0.0559 1.0000 0.0129
-9.250 -0.6294 0.04154 0.03956 -0.0637 1.0000 0.0129
-9.000 -0.6602 0.03247 0.03011 -0.0670 0.9994 0.0116
-8.750 -0.6366 0.02479 0.02170 -0.0745 0.9961 0.0113
-8.500 -0.6063 0.02129 0.01774 -0.0780 0.9943 0.0113
-8.250 -0.5762 0.01936 0.01557 -0.0799 0.9921 0.0115
-8.000 -0.5451 0.01776 0.01374 -0.0816 0.9896 0.0118
-7.750 -0.5131 0.01622 0.01199 -0.0833 0.9876 0.0120
-7.500 -0.4798 0.01505 0.01065 -0.0850 0.9859 0.0122
-7.250 -0.4459 0.01414 0.00961 -0.0866 0.9846 0.0125
-7.000 -0.4111 0.01351 0.00888 -0.0883 0.9835 0.0127
-6.750 -0.3805 0.01223 0.00746 -0.0894 0.9805 0.0130
-6.500 -0.3499 0.01112 0.00623 -0.0904 0.9767 0.0134
-6.250 -0.3178 0.01044 0.00547 -0.0915 0.9736 0.0138
-6.000 -0.2852 0.00989 0.00487 -0.0926 0.9707 0.0142
-5.750 -0.2566 0.00946 0.00440 -0.0928 0.9651 0.0147
-5.500 -0.2274 0.00907 0.00396 -0.0931 0.9594 0.0152
-5.250 -0.1981 0.00873 0.00356 -0.0933 0.9540 0.0160
-5.000 -0.1707 0.00845 0.00324 -0.0931 0.9463 0.0168
-4.750 -0.1426 0.00810 0.00282 -0.0930 0.9396 0.0181
-4.500 -0.1153 0.00781 0.00251 -0.0928 0.9313 0.0205
-4.250 -0.0877 0.00754 0.00223 -0.0926 0.9237 0.0274
-4.000 -0.0604 0.00725 0.00202 -0.0924 0.9153 0.0493
-3.750 -0.0330 0.00710 0.00188 -0.0922 0.9060 0.0609
-3.500 -0.0056 0.00696 0.00175 -0.0919 0.8965 0.0727
-3.250 0.0220 0.00683 0.00162 -0.0917 0.8863 0.0867
-3.000 0.0498 0.00668 0.00151 -0.0916 0.8766 0.1020
-2.750 0.0776 0.00653 0.00139 -0.0915 0.8670 0.1209
-2.500 0.1054 0.00636 0.00127 -0.0914 0.8569 0.1486
-2.250 0.1334 0.00616 0.00117 -0.0914 0.8469 0.1891
-2.000 0.1612 0.00585 0.00107 -0.0915 0.8373 0.2633
-1.750 0.1889 0.00548 0.00099 -0.0916 0.8274 0.3678
-1.500 0.2169 0.00528 0.00095 -0.0916 0.8172 0.4377
-1.250 0.2449 0.00519 0.00094 -0.0915 0.8071 0.4800
-1.000 0.2728 0.00514 0.00093 -0.0914 0.7964 0.5163
-0.750 0.3009 0.00510 0.00093 -0.0913 0.7848 0.5467
-0.500 0.3289 0.00509 0.00093 -0.0911 0.7729 0.5684
-0.250 0.3569 0.00510 0.00093 -0.0910 0.7602 0.5876
0.000 0.3848 0.00512 0.00094 -0.0908 0.7470 0.6036
0.250 0.4127 0.00515 0.00096 -0.0906 0.7328 0.6204
0.500 0.4405 0.00519 0.00098 -0.0904 0.7174 0.6348
0.750 0.4680 0.00522 0.00102 -0.0902 0.7005 0.6552
1.000 0.4955 0.00528 0.00106 -0.0900 0.6816 0.6780
1.250 0.5227 0.00534 0.00112 -0.0897 0.6607 0.6976
1.500 0.5497 0.00545 0.00118 -0.0894 0.6350 0.7154
1.750 0.5765 0.00559 0.00125 -0.0890 0.6042 0.7303
2.000 0.6026 0.00580 0.00133 -0.0886 0.5622 0.7446
2.250 0.6281 0.00609 0.00145 -0.0881 0.5086 0.7591
2.500 0.6538 0.00638 0.00158 -0.0876 0.4618 0.7742
2.750 0.6797 0.00665 0.00172 -0.0872 0.4211 0.7904
3.000 0.7058 0.00686 0.00186 -0.0869 0.3905 0.8081
3.250 0.7319 0.00703 0.00200 -0.0865 0.3640 0.8285
3.500 0.7572 0.00721 0.00214 -0.0859 0.3360 0.8556
3.750 0.7787 0.00721 0.00225 -0.0844 0.3105 0.9350
4.000 0.8077 0.00746 0.00240 -0.0847 0.2837 1.0000
4.250 0.8346 0.00771 0.00257 -0.0845 0.2610 1.0000
4.500 0.8611 0.00800 0.00275 -0.0843 0.2372 1.0000
4.750 0.8872 0.00834 0.00295 -0.0841 0.2098 1.0000
5.000 0.9128 0.00873 0.00319 -0.0837 0.1780 1.0000
5.250 0.9381 0.00916 0.00347 -0.0834 0.1464 1.0000
5.500 0.9631 0.00964 0.00378 -0.0829 0.1166 1.0000
5.750 0.9882 0.01007 0.00410 -0.0825 0.0939 1.0000
6.000 1.0133 0.01051 0.00443 -0.0821 0.0765 1.0000
6.250 1.0388 0.01088 0.00475 -0.0817 0.0658 1.0000
6.500 1.0646 0.01121 0.00506 -0.0814 0.0586 1.0000
6.750 1.0896 0.01164 0.00544 -0.0809 0.0512 1.0000
7.000 1.1154 0.01193 0.00575 -0.0806 0.0479 1.0000
7.250 1.1406 0.01230 0.00611 -0.0801 0.0439 1.0000
7.500 1.1647 0.01282 0.00663 -0.0795 0.0395 1.0000
7.750 1.1905 0.01307 0.00692 -0.0792 0.0381 1.0000
8.000 1.2156 0.01339 0.00725 -0.0788 0.0357 1.0000
8.250 1.2396 0.01385 0.00769 -0.0782 0.0326 1.0000
8.500 1.2630 0.01439 0.00828 -0.0775 0.0304 1.0000
8.750 1.2879 0.01470 0.00862 -0.0771 0.0294 1.0000
9.000 1.3123 0.01504 0.00899 -0.0766 0.0280 1.0000
9.250 1.3361 0.01545 0.00940 -0.0760 0.0262 1.0000
9.500 1.3577 0.01612 0.01009 -0.0751 0.0238 1.0000
9.750 1.3807 0.01657 0.01060 -0.0744 0.0228 1.0000
10.000 1.4044 0.01692 0.01100 -0.0739 0.0218 1.0000
10.250 1.4274 0.01732 0.01142 -0.0732 0.0205 1.0000
10.500 1.4492 0.01784 0.01194 -0.0724 0.0189 1.0000
10.750 1.4685 0.01861 0.01276 -0.0712 0.0172 1.0000
11.000 1.4910 0.01899 0.01318 -0.0705 0.0163 1.0000
11.250 1.5123 0.01947 0.01369 -0.0697 0.0149 1.0000
11.500 1.5286 0.02042 0.01466 -0.0682 0.0129 1.0000
11.750 1.5491 0.02089 0.01519 -0.0672 0.0122 1.0000
12.000 1.5675 0.02153 0.01587 -0.0660 0.0112 1.0000
12.250 1.5829 0.02237 0.01674 -0.0643 0.0102 1.0000
12.500 1.5922 0.02357 0.01803 -0.0618 0.0094 1.0000
12.750 1.6043 0.02428 0.01883 -0.0596 0.0090 1.0000
13.000 1.6137 0.02514 0.01978 -0.0571 0.0087 1.0000
13.250 1.6222 0.02608 0.02079 -0.0547 0.0083 1.0000
13.500 1.6294 0.02715 0.02195 -0.0523 0.0080 1.0000
13.750 1.6352 0.02838 0.02326 -0.0500 0.0077 1.0000
14.000 1.6378 0.02993 0.02490 -0.0476 0.0073 1.0000
14.250 1.6362 0.03190 0.02699 -0.0452 0.0070 1.0000
14.500 1.6277 0.03462 0.02986 -0.0428 0.0068 1.0000
14.750 1.6283 0.03672 0.03208 -0.0414 0.0066 1.0000
15.000 1.6303 0.03882 0.03429 -0.0403 0.0065 1.0000
15.250 1.6301 0.04129 0.03688 -0.0395 0.0064 1.0000
15.500 1.6285 0.04404 0.03975 -0.0391 0.0063 1.0000
15.750 1.6242 0.04732 0.04316 -0.0390 0.0062 1.0000
16.000 1.6187 0.05096 0.04693 -0.0394 0.0061 1.0000
16.250 1.6098 0.05533 0.05145 -0.0404 0.0060 1.0000
16.500 1.5998 0.06019 0.05645 -0.0419 0.0059 1.0000
16.750 1.5864 0.06595 0.06236 -0.0443 0.0059 1.0000
17.000 1.5708 0.07253 0.06910 -0.0474 0.0058 1.0000
17.250 1.5518 0.08016 0.07689 -0.0514 0.0058 1.0000
17.500 1.5301 0.08871 0.08561 -0.0561 0.0058 1.0000
17.750 1.5056 0.09817 0.09523 -0.0614 0.0058 1.0000
18.000 1.4779 0.10854 0.10577 -0.0674 0.0059 1.0000
18.250 1.4493 0.11943 0.11681 -0.0738 0.0059 1.0000
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