S1091 (s1091-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 500,000 Max Cl/Cd: 129.79 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1091-il-500000.txt Download as CSV file: xf-s1091-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3009 0.09918 0.09705 -0.0140 1.0000 0.0076
-7.000 -0.3034 0.09752 0.09542 -0.0124 1.0000 0.0077
-6.750 -0.3095 0.09612 0.09407 -0.0102 1.0000 0.0078
-6.500 -0.2991 0.09338 0.09135 -0.0124 0.9981 0.0080
-6.250 -0.2718 0.08930 0.08725 -0.0189 0.9950 0.0083
-6.000 -0.2444 0.08500 0.08296 -0.0254 0.9909 0.0089
-5.750 -0.2057 0.08064 0.07858 -0.0361 0.9868 0.0096
-5.500 -0.1645 0.07614 0.07405 -0.0474 0.9841 0.0097
-5.250 -0.1329 0.07203 0.06992 -0.0544 0.9783 0.0098
-5.000 -0.1183 0.06779 0.06571 -0.0547 0.9756 0.0103
-4.750 -0.0835 0.06411 0.06201 -0.0614 0.9733 0.0110
-4.500 -0.0516 0.06058 0.05846 -0.0673 0.9679 0.0119
-4.250 -0.0129 0.05664 0.05448 -0.0747 0.9634 0.0126
-4.000 0.0396 0.05233 0.05010 -0.0853 0.9608 0.0134
-3.750 0.0946 0.04799 0.04568 -0.0957 0.9592 0.0137
-3.500 0.1307 0.04441 0.04204 -0.1007 0.9506 0.0138
-3.250 0.1720 0.03928 0.03685 -0.1079 0.9475 0.0143
-3.000 0.2026 0.03667 0.03421 -0.1108 0.9394 0.0150
-2.750 0.2459 0.03337 0.03082 -0.1164 0.9343 0.0160
-2.500 0.2906 0.02976 0.02708 -0.1219 0.9251 0.0176
-2.250 0.3533 0.02517 0.02218 -0.1298 0.9198 0.0195
-0.750 0.5826 0.00960 0.00411 -0.1434 0.8229 0.0211
-0.500 0.6099 0.00903 0.00330 -0.1427 0.8051 0.0205
-0.250 0.6363 0.00850 0.00264 -0.1421 0.7882 0.0218
0.000 0.6624 0.00829 0.00235 -0.1414 0.7724 0.0252
0.250 0.6886 0.00812 0.00205 -0.1407 0.7574 0.0284
0.500 0.7148 0.00798 0.00181 -0.1400 0.7429 0.0369
0.750 0.7403 0.00771 0.00182 -0.1394 0.7285 0.1619
1.000 0.7657 0.00764 0.00187 -0.1387 0.7141 0.2436
1.250 0.7907 0.00755 0.00198 -0.1381 0.6997 0.3637
1.500 0.8150 0.00736 0.00211 -0.1373 0.6849 0.5346
1.750 0.8447 0.00666 0.00211 -0.1376 0.6691 1.0000
2.000 0.8700 0.00680 0.00213 -0.1368 0.6528 1.0000
2.250 0.8952 0.00695 0.00217 -0.1360 0.6357 1.0000
2.500 0.9200 0.00713 0.00222 -0.1352 0.6169 1.0000
2.750 0.9449 0.00728 0.00230 -0.1344 0.5958 1.0000
3.000 0.9693 0.00748 0.00237 -0.1335 0.5732 1.0000
3.250 0.9932 0.00770 0.00246 -0.1326 0.5420 1.0000
3.500 1.0161 0.00801 0.00257 -0.1314 0.5026 1.0000
3.750 1.0389 0.00836 0.00273 -0.1303 0.4633 1.0000
4.000 1.0617 0.00875 0.00295 -0.1293 0.4275 1.0000
4.250 1.0844 0.00917 0.00318 -0.1283 0.3906 1.0000
4.500 1.1072 0.00959 0.00342 -0.1273 0.3572 1.0000
4.750 1.1302 0.00999 0.00368 -0.1264 0.3260 1.0000
5.000 1.1533 0.01040 0.00394 -0.1255 0.2972 1.0000
5.250 1.1762 0.01082 0.00425 -0.1246 0.2678 1.0000
5.500 1.1988 0.01127 0.00456 -0.1236 0.2378 1.0000
5.750 1.2210 0.01177 0.00491 -0.1226 0.2074 1.0000
6.000 1.2429 0.01230 0.00529 -0.1216 0.1787 1.0000
6.250 1.2646 0.01284 0.00571 -0.1205 0.1534 1.0000
6.500 1.2859 0.01341 0.00616 -0.1194 0.1314 1.0000
6.750 1.3076 0.01394 0.00661 -0.1183 0.1139 1.0000
7.000 1.3290 0.01448 0.00709 -0.1172 0.1007 1.0000
7.250 1.3500 0.01506 0.00764 -0.1161 0.0911 1.0000
7.500 1.3717 0.01554 0.00813 -0.1150 0.0846 1.0000
7.750 1.3915 0.01620 0.00879 -0.1136 0.0789 1.0000
8.000 1.4133 0.01664 0.00930 -0.1125 0.0757 1.0000
8.250 1.4341 0.01716 0.00987 -0.1113 0.0725 1.0000
8.500 1.4523 0.01791 0.01064 -0.1097 0.0691 1.0000
8.750 1.4696 0.01873 0.01154 -0.1079 0.0668 1.0000
9.000 1.4898 0.01924 0.01215 -0.1066 0.0654 1.0000
9.250 1.5094 0.01979 0.01278 -0.1053 0.0636 1.0000
9.500 1.5280 0.02039 0.01348 -0.1038 0.0619 1.0000
9.750 1.5464 0.02096 0.01411 -0.1023 0.0596 1.0000
10.000 1.5604 0.02193 0.01511 -0.1002 0.0568 1.0000
10.250 1.5785 0.02243 0.01570 -0.0988 0.0542 1.0000
10.500 1.5990 0.02261 0.01596 -0.0977 0.0516 1.0000
10.750 1.6167 0.02298 0.01639 -0.0961 0.0489 1.0000
11.000 1.6284 0.02377 0.01721 -0.0937 0.0456 1.0000
11.250 1.6490 0.02391 0.01743 -0.0927 0.0424 1.0000
11.500 1.6694 0.02407 0.01760 -0.0918 0.0379 1.0000
11.750 1.6841 0.02466 0.01822 -0.0899 0.0336 1.0000
12.000 1.6955 0.02555 0.01893 -0.0879 0.0182 1.0000
12.250 1.6846 0.02820 0.02150 -0.0828 0.0056 1.0000
12.500 1.6837 0.03014 0.02357 -0.0793 0.0038 1.0000
12.750 1.6855 0.03189 0.02549 -0.0764 0.0031 1.0000
13.000 1.6843 0.03398 0.02774 -0.0735 0.0026 1.0000
13.250 1.6803 0.03643 0.03040 -0.0708 0.0024 1.0000
13.500 1.6796 0.03866 0.03281 -0.0687 0.0022 1.0000
13.750 1.6760 0.04132 0.03566 -0.0669 0.0021 1.0000
14.000 1.6707 0.04432 0.03885 -0.0654 0.0020 1.0000
14.250 1.6638 0.04772 0.04243 -0.0645 0.0019 1.0000
14.500 1.6559 0.05148 0.04635 -0.0640 0.0019 1.0000
14.750 1.6454 0.05583 0.05088 -0.0640 0.0019 1.0000
15.000 1.6335 0.06067 0.05590 -0.0647 0.0018 1.0000
15.250 1.6193 0.06621 0.06162 -0.0660 0.0018 1.0000
15.500 1.6044 0.07219 0.06779 -0.0679 0.0018 1.0000
15.750 1.5872 0.07901 0.07480 -0.0706 0.0018 1.0000
16.000 1.5687 0.08657 0.08254 -0.0739 0.0018 1.0000
16.250 1.5493 0.09476 0.09092 -0.0779 0.0018 1.0000
16.500 1.5279 0.10382 0.10016 -0.0826 0.0018 1.0000
16.750 1.5060 0.11330 0.10982 -0.0877 0.0018 1.0000
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Polar data table (+)
Polar graphs
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