S1091 (s1091-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 100,000 Max Cl/Cd: 70.57 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1091-il-100000.txt Download as CSV file: xf-s1091-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S1091
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2904 0.09946 0.09487 -0.0170 1.0000 0.0424
-6.500 -0.2919 0.09764 0.09312 -0.0157 1.0000 0.0434
-6.250 -0.2910 0.09570 0.09126 -0.0151 1.0000 0.0443
-6.000 -0.2901 0.09371 0.08933 -0.0147 1.0000 0.0457
-5.750 -0.2887 0.09185 0.08754 -0.0147 1.0000 0.0470
-5.500 -0.2861 0.09020 0.08596 -0.0153 1.0000 0.0482
-5.250 -0.2800 0.08917 0.08499 -0.0179 1.0000 0.0495
-5.000 -0.2640 0.08898 0.08481 -0.0249 1.0000 0.0503
-4.750 -0.2435 0.08791 0.08373 -0.0314 1.0000 0.0506
-4.500 -0.2502 0.08304 0.07898 -0.0268 1.0000 0.0513
-4.250 -0.2553 0.07953 0.07555 -0.0220 1.0000 0.0523
-4.000 -0.2529 0.07698 0.07305 -0.0203 1.0000 0.0537
-3.750 -0.2450 0.07467 0.07077 -0.0206 1.0000 0.0555
-3.500 -0.2321 0.07238 0.06849 -0.0225 1.0000 0.0580
-3.250 -0.1467 0.07119 0.06700 -0.0448 0.9972 0.0641
-3.000 -0.1380 0.06513 0.06106 -0.0430 0.9921 0.0657
-2.750 -0.1071 0.06136 0.05729 -0.0463 0.9861 0.0701
-2.500 -0.0289 0.05763 0.05331 -0.0630 0.9795 0.0791
-2.250 -0.0038 0.05384 0.04957 -0.0642 0.9736 0.0838
-2.000 0.0548 0.05033 0.04589 -0.0744 0.9667 0.0949
-1.750 0.1056 0.04709 0.04251 -0.0818 0.9609 0.1094
-1.500 0.1518 0.04412 0.03942 -0.0877 0.9539 0.1240
-1.250 0.2158 0.04209 0.03704 -0.0969 0.9479 0.1505
-1.000 0.2511 0.03871 0.03368 -0.0998 0.9408 0.1661
-0.750 0.2937 0.03597 0.03090 -0.1034 0.9346 0.1855
-0.500 0.3843 0.02989 0.02347 -0.1146 0.9332 0.0932
-0.250 0.4281 0.02700 0.02002 -0.1170 0.9254 0.0773
0.000 0.4783 0.02438 0.01696 -0.1206 0.9205 0.0724
0.250 0.5182 0.02278 0.01492 -0.1220 0.9116 0.0724
0.500 0.5674 0.02131 0.01323 -0.1252 0.9060 0.0847
0.750 0.6043 0.02030 0.01218 -0.1261 0.8959 0.1052
1.000 0.6573 0.01858 0.01136 -0.1302 0.8917 0.3933
1.250 0.6965 0.01709 0.01062 -0.1317 0.8816 1.0000
1.500 0.7392 0.01680 0.01004 -0.1337 0.8723 1.0000
1.750 0.7848 0.01636 0.00940 -0.1362 0.8637 1.0000
2.000 0.8209 0.01616 0.00907 -0.1370 0.8510 1.0000
2.250 0.8572 0.01593 0.00874 -0.1377 0.8377 1.0000
2.500 0.8928 0.01571 0.00844 -0.1382 0.8231 1.0000
3.000 0.9576 0.01545 0.00805 -0.1379 0.7887 1.0000
3.250 0.9850 0.01547 0.00800 -0.1369 0.7677 1.0000
3.500 1.0142 0.01545 0.00788 -0.1361 0.7468 1.0000
3.750 1.0385 0.01555 0.00793 -0.1345 0.7225 1.0000
4.000 1.0630 0.01566 0.00802 -0.1330 0.6972 1.0000
4.250 1.0870 0.01578 0.00805 -0.1313 0.6704 1.0000
4.500 1.1098 0.01594 0.00813 -0.1296 0.6413 1.0000
4.750 1.1316 0.01612 0.00823 -0.1277 0.6097 1.0000
5.000 1.1528 0.01634 0.00835 -0.1257 0.5758 1.0000
5.250 1.1728 0.01662 0.00859 -0.1236 0.5372 1.0000
5.500 1.1920 0.01699 0.00881 -0.1215 0.4956 1.0000
5.750 1.2101 0.01753 0.00912 -0.1193 0.4511 1.0000
6.000 1.2274 0.01825 0.00960 -0.1171 0.4056 1.0000
6.250 1.2435 0.01913 0.01020 -0.1148 0.3595 1.0000
6.500 1.2588 0.02015 0.01100 -0.1125 0.3133 1.0000
6.750 1.2735 0.02133 0.01190 -0.1103 0.2692 1.0000
7.000 1.2885 0.02260 0.01292 -0.1081 0.2321 1.0000
7.250 1.3046 0.02391 0.01401 -0.1062 0.2042 1.0000
7.500 1.3223 0.02525 0.01520 -0.1046 0.1838 1.0000
7.750 1.3420 0.02662 0.01655 -0.1032 0.1690 1.0000
8.000 1.3637 0.02812 0.01794 -0.1023 0.1580 1.0000
8.250 1.3862 0.02949 0.01939 -0.1014 0.1490 1.0000
8.500 1.4100 0.03114 0.02111 -0.1007 0.1418 1.0000
8.750 1.4326 0.03256 0.02261 -0.1000 0.1349 1.0000
9.000 1.4561 0.03439 0.02457 -0.0994 0.1293 1.0000
9.250 1.4781 0.03614 0.02660 -0.0984 0.1250 1.0000
9.500 1.5012 0.03804 0.02862 -0.0978 0.1213 1.0000
9.750 1.5255 0.04083 0.03153 -0.0976 0.1182 1.0000
10.000 1.5392 0.04296 0.03424 -0.0954 0.1157 1.0000
10.250 1.5529 0.04512 0.03681 -0.0935 0.1121 1.0000
10.500 1.5696 0.04733 0.03924 -0.0922 0.1088 1.0000
10.750 1.5866 0.05041 0.04250 -0.0912 0.1064 1.0000
11.000 1.5914 0.05407 0.04662 -0.0887 0.1045 1.0000
11.250 1.5868 0.05717 0.05033 -0.0849 0.1025 1.0000
11.500 1.5803 0.06050 0.05414 -0.0813 0.1003 1.0000
11.750 1.5726 0.06397 0.05799 -0.0779 0.0985 1.0000
12.000 1.5661 0.06728 0.06158 -0.0749 0.0967 1.0000
12.250 1.5866 0.07055 0.06478 -0.0752 0.0919 1.0000
12.500 1.5611 0.07409 0.06868 -0.0706 0.0916 1.0000
12.750 1.5336 0.07801 0.07288 -0.0667 0.0914 1.0000
13.000 1.5053 0.08269 0.07776 -0.0642 0.0915 1.0000
13.250 1.4766 0.08820 0.08349 -0.0633 0.0917 1.0000
13.500 1.4482 0.09459 0.09006 -0.0639 0.0920 1.0000
13.750 1.4208 0.10190 0.09752 -0.0657 0.0923 1.0000
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Polar data table (+)
Polar graphs
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