S2091-101-83 (s2091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2091-il-1000000-n5.txt Download as CSV file: xf-s2091-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4354 0.14382 0.14206 -0.0060 1.0000 0.0046
-13.000 -0.4319 0.13921 0.13746 -0.0079 1.0000 0.0047
-12.000 -0.8483 0.03081 0.02824 -0.0797 0.9746 0.0051
-11.750 -0.8325 0.02754 0.02469 -0.0821 0.9495 0.0052
-11.500 -0.8195 0.02528 0.02218 -0.0820 0.9312 0.0053
-11.250 -0.8024 0.02367 0.02036 -0.0818 0.9177 0.0053
-11.000 -0.7835 0.02220 0.01869 -0.0816 0.9066 0.0054
-10.750 -0.7631 0.02092 0.01723 -0.0813 0.8966 0.0055
-10.500 -0.7410 0.01980 0.01594 -0.0811 0.8871 0.0056
-10.250 -0.7180 0.01881 0.01478 -0.0809 0.8787 0.0058
-10.000 -0.6943 0.01790 0.01371 -0.0807 0.8700 0.0059
-9.750 -0.6699 0.01706 0.01273 -0.0806 0.8622 0.0061
-9.500 -0.6451 0.01630 0.01182 -0.0804 0.8540 0.0062
-9.250 -0.6196 0.01561 0.01099 -0.0803 0.8465 0.0064
-9.000 -0.5939 0.01500 0.01024 -0.0801 0.8385 0.0065
-8.750 -0.5676 0.01446 0.00959 -0.0800 0.8312 0.0066
-8.500 -0.5417 0.01374 0.00875 -0.0799 0.8232 0.0070
-8.250 -0.5151 0.01323 0.00815 -0.0798 0.8162 0.0074
-8.000 -0.4881 0.01279 0.00762 -0.0797 0.8084 0.0077
-7.750 -0.4610 0.01239 0.00713 -0.0796 0.8014 0.0080
-7.500 -0.4337 0.01199 0.00664 -0.0795 0.7935 0.0083
-7.250 -0.4064 0.01162 0.00617 -0.0794 0.7864 0.0087
-7.000 -0.3787 0.01128 0.00575 -0.0793 0.7786 0.0090
-6.750 -0.3513 0.01089 0.00529 -0.0792 0.7714 0.0096
-6.500 -0.3235 0.01061 0.00497 -0.0792 0.7634 0.0103
-6.250 -0.2956 0.01036 0.00464 -0.0791 0.7561 0.0110
-6.000 -0.2676 0.01011 0.00433 -0.0791 0.7481 0.0116
-5.750 -0.2397 0.00986 0.00402 -0.0790 0.7404 0.0125
-5.500 -0.2115 0.00966 0.00379 -0.0790 0.7324 0.0136
-5.250 -0.1834 0.00949 0.00356 -0.0789 0.7246 0.0147
-5.000 -0.1552 0.00927 0.00329 -0.0789 0.7165 0.0157
-4.750 -0.1270 0.00908 0.00306 -0.0789 0.7087 0.0168
-4.500 -0.0987 0.00892 0.00285 -0.0788 0.7003 0.0179
-4.250 -0.0703 0.00879 0.00265 -0.0788 0.6923 0.0188
-4.000 -0.0420 0.00859 0.00243 -0.0788 0.6836 0.0205
-3.750 -0.0136 0.00846 0.00226 -0.0788 0.6754 0.0221
-3.500 0.0147 0.00834 0.00208 -0.0788 0.6663 0.0237
-3.250 0.0432 0.00819 0.00192 -0.0788 0.6575 0.0264
-3.000 0.0716 0.00809 0.00178 -0.0787 0.6482 0.0296
-2.750 0.1000 0.00798 0.00165 -0.0787 0.6383 0.0345
-2.500 0.1284 0.00787 0.00155 -0.0787 0.6291 0.0415
-2.000 0.1853 0.00772 0.00137 -0.0788 0.6091 0.0569
-1.750 0.2137 0.00767 0.00130 -0.0788 0.5992 0.0634
-1.250 0.2706 0.00757 0.00118 -0.0788 0.5779 0.0825
-1.000 0.2989 0.00752 0.00113 -0.0788 0.5672 0.0986
-0.750 0.3272 0.00745 0.00110 -0.0788 0.5559 0.1259
-0.500 0.3554 0.00737 0.00108 -0.0789 0.5442 0.1602
-0.250 0.3837 0.00730 0.00106 -0.0789 0.5327 0.1952
0.000 0.4118 0.00724 0.00106 -0.0790 0.5215 0.2336
0.250 0.4399 0.00716 0.00107 -0.0790 0.5099 0.2854
0.500 0.4679 0.00709 0.00109 -0.0791 0.4979 0.3384
0.750 0.4960 0.00704 0.00112 -0.0791 0.4859 0.3881
1.000 0.5239 0.00698 0.00117 -0.0792 0.4740 0.4464
1.250 0.5514 0.00685 0.00124 -0.0792 0.4621 0.5411
1.500 0.5787 0.00674 0.00132 -0.0791 0.4495 0.6315
1.750 0.6056 0.00663 0.00140 -0.0789 0.4366 0.7192
2.000 0.6301 0.00642 0.00150 -0.0781 0.4247 0.8408
2.250 0.6606 0.00627 0.00155 -0.0784 0.4119 1.0000
2.500 0.6884 0.00641 0.00162 -0.0783 0.3990 1.0000
2.750 0.7161 0.00657 0.00171 -0.0783 0.3868 1.0000
3.000 0.7437 0.00673 0.00180 -0.0782 0.3738 1.0000
3.250 0.7713 0.00690 0.00190 -0.0781 0.3607 1.0000
3.500 0.7988 0.00706 0.00200 -0.0781 0.3477 1.0000
3.750 0.8262 0.00724 0.00212 -0.0780 0.3351 1.0000
4.000 0.8535 0.00742 0.00225 -0.0779 0.3228 1.0000
4.250 0.8806 0.00762 0.00238 -0.0778 0.3094 1.0000
4.500 0.9077 0.00783 0.00254 -0.0777 0.2968 1.0000
4.750 0.9345 0.00805 0.00269 -0.0776 0.2839 1.0000
5.000 0.9613 0.00827 0.00286 -0.0775 0.2709 1.0000
5.250 0.9879 0.00851 0.00304 -0.0773 0.2571 1.0000
5.500 1.0145 0.00874 0.00322 -0.0772 0.2450 1.0000
5.750 1.0410 0.00898 0.00342 -0.0770 0.2331 1.0000
6.000 1.0670 0.00926 0.00363 -0.0768 0.2198 1.0000
6.250 1.0930 0.00954 0.00386 -0.0766 0.2072 1.0000
6.500 1.1185 0.00985 0.00410 -0.0763 0.1930 1.0000
6.750 1.1438 0.01018 0.00437 -0.0760 0.1785 1.0000
7.000 1.1690 0.01051 0.00464 -0.0757 0.1660 1.0000
7.500 1.2188 0.01119 0.00522 -0.0750 0.1428 1.0000
7.750 1.2431 0.01157 0.00555 -0.0746 0.1303 1.0000
8.000 1.2669 0.01198 0.00590 -0.0741 0.1178 1.0000
8.250 1.2903 0.01241 0.00628 -0.0736 0.1054 1.0000
8.500 1.3134 0.01286 0.00668 -0.0730 0.0939 1.0000
8.750 1.3362 0.01331 0.00709 -0.0724 0.0839 1.0000
9.000 1.3581 0.01382 0.00754 -0.0717 0.0730 1.0000
9.250 1.3795 0.01434 0.00802 -0.0710 0.0633 1.0000
9.500 1.4003 0.01488 0.00852 -0.0701 0.0552 1.0000
9.750 1.4211 0.01540 0.00902 -0.0692 0.0488 1.0000
10.000 1.4419 0.01588 0.00950 -0.0684 0.0443 1.0000
10.250 1.4611 0.01644 0.01004 -0.0673 0.0393 1.0000
10.500 1.4806 0.01694 0.01056 -0.0663 0.0360 1.0000
10.750 1.4981 0.01754 0.01116 -0.0650 0.0322 1.0000
11.000 1.5157 0.01808 0.01172 -0.0637 0.0298 1.0000
11.250 1.5301 0.01863 0.01230 -0.0618 0.0276 1.0000
11.500 1.5412 0.01930 0.01298 -0.0595 0.0254 1.0000
11.750 1.5534 0.01993 0.01366 -0.0575 0.0238 1.0000
12.000 1.5647 0.02067 0.01443 -0.0556 0.0221 1.0000
12.250 1.5741 0.02155 0.01534 -0.0536 0.0202 1.0000
12.500 1.5851 0.02241 0.01625 -0.0519 0.0191 1.0000
12.750 1.5952 0.02337 0.01726 -0.0502 0.0179 1.0000
13.000 1.6039 0.02448 0.01841 -0.0486 0.0167 1.0000
13.250 1.6121 0.02569 0.01966 -0.0471 0.0156 1.0000
13.500 1.6206 0.02692 0.02096 -0.0458 0.0145 1.0000
13.750 1.6269 0.02839 0.02247 -0.0444 0.0133 1.0000
14.000 1.6325 0.02999 0.02412 -0.0432 0.0123 1.0000
14.250 1.6395 0.03153 0.02574 -0.0422 0.0120 1.0000
14.500 1.6450 0.03328 0.02755 -0.0413 0.0112 1.0000
14.750 1.6497 0.03517 0.02951 -0.0406 0.0108 1.0000
15.000 1.6523 0.03733 0.03175 -0.0399 0.0102 1.0000
15.250 1.6542 0.03966 0.03415 -0.0394 0.0098 1.0000
15.500 1.6561 0.04208 0.03665 -0.0390 0.0094 1.0000
15.750 1.6575 0.04461 0.03928 -0.0389 0.0091 1.0000
16.000 1.6578 0.04738 0.04214 -0.0388 0.0087 1.0000
16.250 1.6569 0.05042 0.04527 -0.0391 0.0085 1.0000
16.500 1.6547 0.05372 0.04866 -0.0394 0.0081 1.0000
16.750 1.6512 0.05732 0.05235 -0.0401 0.0079 1.0000
17.000 1.6460 0.06131 0.05642 -0.0410 0.0075 1.0000
17.250 1.6397 0.06557 0.06078 -0.0421 0.0072 1.0000
17.500 1.6348 0.06978 0.06511 -0.0434 0.0070 1.0000
17.750 1.6283 0.07435 0.06979 -0.0449 0.0069 1.0000
18.000 1.6206 0.07922 0.07477 -0.0467 0.0068 1.0000
18.250 1.6115 0.08444 0.08011 -0.0487 0.0066 1.0000
18.500 1.6018 0.08990 0.08568 -0.0509 0.0065 1.0000
18.750 1.5904 0.09578 0.09167 -0.0535 0.0063 1.0000
19.000 1.5783 0.10189 0.09790 -0.0562 0.0062 1.0000
19.250 1.5659 0.10818 0.10431 -0.0592 0.0061 1.0000
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Polar data table (+)
Polar graphs
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