S1091 (s1091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.99 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1091-il-1000000.txt Download as CSV file: xf-s1091-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2682 0.12756 0.12598 -0.0192 1.0000 0.0043
-11.000 -0.2651 0.12491 0.12334 -0.0193 1.0000 0.0043
-10.750 -0.2621 0.12224 0.12067 -0.0194 1.0000 0.0044
-8.500 -0.2192 0.09433 0.09284 -0.0245 0.9978 0.0044
-8.250 -0.2076 0.09039 0.08891 -0.0265 0.9968 0.0045
-8.000 -0.1954 0.08666 0.08519 -0.0289 0.9958 0.0046
-7.750 -0.1824 0.08292 0.08145 -0.0316 0.9950 0.0048
-7.500 -0.1710 0.07933 0.07786 -0.0339 0.9934 0.0048
-7.250 -0.1589 0.07572 0.07426 -0.0363 0.9913 0.0050
-7.000 -0.1455 0.07202 0.07055 -0.0391 0.9893 0.0051
-6.750 -0.1307 0.06818 0.06672 -0.0424 0.9874 0.0054
-6.500 -0.1148 0.06422 0.06276 -0.0461 0.9857 0.0057
-6.250 -0.1022 0.06075 0.05930 -0.0488 0.9820 0.0060
-6.000 -0.1682 0.07761 0.07607 -0.0459 0.9855 0.0054
-5.750 -0.1418 0.07380 0.07226 -0.0518 0.9829 0.0059
-5.500 -0.1151 0.07003 0.06848 -0.0574 0.9783 0.0064
-5.250 -0.0719 0.06523 0.06365 -0.0686 0.9753 0.0067
-4.500 0.0172 0.05404 0.05242 -0.0847 0.9651 0.0074
-4.250 0.0555 0.05045 0.04880 -0.0916 0.9621 0.0078
-4.000 0.0989 0.04658 0.04489 -0.0994 0.9599 0.0083
-3.750 0.1293 0.04334 0.04162 -0.1035 0.9497 0.0087
-3.500 0.1740 0.03938 0.03759 -0.1106 0.9411 0.0093
-3.250 0.2324 0.03483 0.03292 -0.1204 0.9332 0.0096
-3.000 0.2901 0.03020 0.02814 -0.1297 0.9204 0.0097
-1.750 0.4744 0.01338 0.00966 -0.1448 0.7999 0.0127
-1.500 0.5040 0.00988 0.00534 -0.1441 0.7824 0.0094
-1.250 0.5300 0.00890 0.00406 -0.1435 0.7654 0.0110
-1.000 0.5559 0.00850 0.00351 -0.1429 0.7496 0.0118
-0.750 0.5820 0.00837 0.00325 -0.1422 0.7347 0.0133
-0.500 0.6083 0.00797 0.00271 -0.1416 0.7210 0.0136
-0.250 0.6346 0.00760 0.00222 -0.1409 0.7076 0.0139
0.000 0.6607 0.00709 0.00158 -0.1403 0.6945 0.0162
0.250 0.6869 0.00700 0.00142 -0.1398 0.6811 0.0185
0.500 0.7132 0.00692 0.00124 -0.1392 0.6681 0.0212
0.750 0.7394 0.00687 0.00114 -0.1386 0.6547 0.0306
1.000 0.7651 0.00670 0.00118 -0.1381 0.6407 0.1365
1.250 0.7909 0.00666 0.00123 -0.1375 0.6256 0.2012
1.500 0.8166 0.00665 0.00129 -0.1370 0.6096 0.2665
1.750 0.8418 0.00660 0.00140 -0.1364 0.5920 0.3824
2.000 0.8666 0.00654 0.00154 -0.1357 0.5719 0.5211
2.250 0.8950 0.00585 0.00163 -0.1360 0.5476 1.0000
2.500 0.9197 0.00608 0.00170 -0.1352 0.5149 1.0000
2.750 0.9432 0.00643 0.00181 -0.1342 0.4682 1.0000
3.000 0.9671 0.00676 0.00195 -0.1334 0.4310 1.0000
3.250 0.9914 0.00706 0.00209 -0.1326 0.3993 1.0000
3.500 1.0156 0.00740 0.00225 -0.1318 0.3652 1.0000
3.750 1.0398 0.00772 0.00241 -0.1311 0.3349 1.0000
4.000 1.0643 0.00801 0.00260 -0.1304 0.3099 1.0000
4.250 1.0885 0.00832 0.00278 -0.1297 0.2845 1.0000
4.500 1.1127 0.00864 0.00297 -0.1290 0.2591 1.0000
4.750 1.1367 0.00898 0.00318 -0.1282 0.2331 1.0000
5.000 1.1603 0.00935 0.00341 -0.1274 0.2072 1.0000
5.250 1.1838 0.00973 0.00368 -0.1266 0.1825 1.0000
5.500 1.2069 0.01014 0.00396 -0.1257 0.1595 1.0000
5.750 1.2304 0.01051 0.00424 -0.1249 0.1397 1.0000
6.000 1.2533 0.01093 0.00454 -0.1240 0.1208 1.0000
6.250 1.2764 0.01132 0.00486 -0.1232 0.1054 1.0000
6.500 1.2997 0.01169 0.00518 -0.1223 0.0937 1.0000
6.750 1.3230 0.01204 0.00549 -0.1215 0.0847 1.0000
7.000 1.3463 0.01240 0.00583 -0.1207 0.0770 1.0000
7.250 1.3690 0.01280 0.00620 -0.1198 0.0706 1.0000
7.500 1.3920 0.01316 0.00658 -0.1189 0.0663 1.0000
7.750 1.4153 0.01347 0.00693 -0.1181 0.0637 1.0000
8.000 1.4378 0.01386 0.00732 -0.1172 0.0606 1.0000
8.250 1.4591 0.01437 0.00785 -0.1160 0.0569 1.0000
8.500 1.4809 0.01480 0.00833 -0.1150 0.0550 1.0000
8.750 1.5039 0.01508 0.00866 -0.1142 0.0538 1.0000
9.000 1.5265 0.01538 0.00900 -0.1133 0.0517 1.0000
9.250 1.5480 0.01578 0.00943 -0.1123 0.0498 1.0000
9.500 1.5679 0.01633 0.00997 -0.1110 0.0458 1.0000
9.750 1.5905 0.01657 0.01025 -0.1102 0.0435 1.0000
10.000 1.6126 0.01685 0.01057 -0.1094 0.0415 1.0000
10.250 1.6332 0.01725 0.01097 -0.1083 0.0388 1.0000
10.500 1.6518 0.01782 0.01154 -0.1069 0.0346 1.0000
10.750 1.6729 0.01812 0.01188 -0.1059 0.0313 1.0000
11.000 1.6868 0.01904 0.01264 -0.1038 0.0190 1.0000
11.250 1.6861 0.02113 0.01460 -0.0994 0.0030 1.0000
11.500 1.6944 0.02219 0.01575 -0.0962 0.0017 1.0000
11.750 1.7028 0.02320 0.01689 -0.0931 0.0012 1.0000
12.000 1.7113 0.02420 0.01800 -0.0902 0.0010 1.0000
12.250 1.7185 0.02529 0.01922 -0.0872 0.0009 1.0000
12.500 1.7246 0.02649 0.02054 -0.0842 0.0008 1.0000
12.750 1.7268 0.02804 0.02223 -0.0809 0.0007 1.0000
13.000 1.7276 0.02973 0.02410 -0.0777 0.0007 1.0000
13.250 1.7268 0.03160 0.02613 -0.0746 0.0007 1.0000
13.500 1.7235 0.03378 0.02848 -0.0716 0.0007 1.0000
13.750 1.7162 0.03646 0.03132 -0.0688 0.0006 1.0000
14.000 1.7072 0.03950 0.03454 -0.0665 0.0006 1.0000
14.250 1.6965 0.04297 0.03820 -0.0649 0.0006 1.0000
14.500 1.6876 0.04654 0.04192 -0.0639 0.0006 1.0000
14.750 1.6772 0.05059 0.04612 -0.0634 0.0006 1.0000
15.000 1.6651 0.05519 0.05088 -0.0637 0.0006 1.0000
15.250 1.6520 0.06024 0.05610 -0.0645 0.0006 1.0000
15.500 1.6360 0.06615 0.06217 -0.0661 0.0006 1.0000
15.750 1.6191 0.07262 0.06880 -0.0683 0.0006 1.0000
16.000 1.5995 0.08010 0.07645 -0.0715 0.0006 1.0000
16.250 1.5785 0.08843 0.08496 -0.0754 0.0006 1.0000
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Polar data table (+)
Polar graphs
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