HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 100,000 Max Cl/Cd: 60.7 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1712-il-100000.txt Download as CSV file: xf-hs1712-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-712 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4120 0.11162 0.10706 -0.0201 1.0000 0.1026
-7.500 -0.4395 0.11044 0.10600 -0.0202 1.0000 0.1042
-7.250 -0.4584 0.10684 0.10247 -0.0290 1.0000 0.1054
-7.000 -0.4488 0.10341 0.09908 -0.0211 1.0000 0.1066
-6.750 -0.4434 0.10083 0.09653 -0.0177 1.0000 0.1086
-6.500 -0.4422 0.09829 0.09402 -0.0170 1.0000 0.1118
-6.250 -0.4403 0.09290 0.08851 -0.0358 1.0000 0.1187
-6.000 -0.4396 0.08997 0.08572 -0.0279 1.0000 0.1201
-5.750 -0.4358 0.08795 0.08377 -0.0236 1.0000 0.1225
-5.500 -0.4116 0.08292 0.07844 -0.0397 1.0000 0.1337
-5.250 -0.4087 0.07966 0.07532 -0.0354 1.0000 0.1350
-5.000 -0.4026 0.07733 0.07306 -0.0326 1.0000 0.1371
-4.750 -0.3660 0.07280 0.06817 -0.0448 0.9994 0.1504
-4.500 -0.3392 0.06903 0.06451 -0.0451 0.9944 0.1536
-4.250 -0.2374 0.04722 0.04082 -0.0731 0.9941 0.0940
-4.000 -0.1872 0.04261 0.03566 -0.0794 0.9895 0.0921
-3.750 -0.1323 0.03856 0.03062 -0.0858 0.9859 0.0936
-3.500 -0.0873 0.03731 0.02937 -0.0901 0.9810 0.0990
-3.250 -0.0395 0.03555 0.02687 -0.0941 0.9753 0.1053
-3.000 0.0085 0.03478 0.02608 -0.0986 0.9714 0.1148
-2.750 0.0468 0.03391 0.02505 -0.1011 0.9632 0.1238
-2.500 0.0950 0.03338 0.02438 -0.1052 0.9590 0.1371
-2.250 0.1296 0.03301 0.02388 -0.1069 0.9503 0.1503
-2.000 0.1743 0.03255 0.02347 -0.1104 0.9460 0.1698
-1.750 0.2097 0.03221 0.02323 -0.1122 0.9382 0.1984
-1.500 0.2526 0.03179 0.02283 -0.1154 0.9323 0.2420
-1.250 0.3008 0.03126 0.02253 -0.1196 0.9290 0.2877
-1.000 0.3277 0.03101 0.02242 -0.1199 0.9184 0.3227
-0.750 0.3734 0.03048 0.02222 -0.1236 0.9145 0.3885
-0.500 0.4007 0.02940 0.02251 -0.1234 0.9072 0.7045
-0.250 0.4253 0.02851 0.02174 -0.1214 0.8988 1.0000
0.000 0.4551 0.02855 0.02156 -0.1218 0.8877 1.0000
0.250 0.5031 0.02811 0.02090 -0.1253 0.8822 1.0000
0.500 0.5313 0.02810 0.02078 -0.1254 0.8706 1.0000
0.750 0.5793 0.02749 0.02002 -0.1287 0.8657 1.0000
1.000 0.6060 0.02751 0.01997 -0.1285 0.8541 1.0000
1.250 0.6526 0.02681 0.01918 -0.1315 0.8495 1.0000
1.500 0.6807 0.02675 0.01907 -0.1314 0.8385 1.0000
1.750 0.7273 0.02583 0.01809 -0.1342 0.8339 1.0000
2.000 0.7580 0.02552 0.01776 -0.1342 0.8233 1.0000
2.250 0.8058 0.02433 0.01654 -0.1370 0.8186 1.0000
2.500 0.8405 0.02376 0.01597 -0.1376 0.8083 1.0000
2.750 0.8956 0.02241 0.01460 -0.1419 0.8030 1.0000
3.000 0.9374 0.02163 0.01383 -0.1438 0.7922 1.0000
3.250 0.9815 0.02081 0.01300 -0.1461 0.7799 1.0000
3.500 1.0108 0.02052 0.01272 -0.1457 0.7613 1.0000
3.750 1.0476 0.01993 0.01211 -0.1466 0.7425 1.0000
4.000 1.0955 0.01921 0.01127 -0.1496 0.7223 1.0000
4.250 1.1310 0.01912 0.01104 -0.1504 0.6955 1.0000
4.500 1.1622 0.01922 0.01100 -0.1504 0.6660 1.0000
4.750 1.1828 0.01952 0.01122 -0.1485 0.6338 1.0000
5.000 1.2046 0.01985 0.01140 -0.1469 0.6018 1.0000
5.250 1.2267 0.02021 0.01158 -0.1454 0.5718 1.0000
5.500 1.2465 0.02069 0.01194 -0.1436 0.5427 1.0000
5.750 1.2660 0.02120 0.01234 -0.1418 0.5167 1.0000
6.000 1.2865 0.02175 0.01276 -0.1403 0.4940 1.0000
6.250 1.3076 0.02235 0.01325 -0.1390 0.4737 1.0000
6.500 1.3289 0.02299 0.01379 -0.1377 0.4551 1.0000
6.750 1.3500 0.02366 0.01439 -0.1365 0.4377 1.0000
7.000 1.3707 0.02435 0.01501 -0.1352 0.4211 1.0000
7.250 1.3914 0.02505 0.01567 -0.1340 0.4056 1.0000
7.500 1.4131 0.02579 0.01633 -0.1330 0.3913 1.0000
7.750 1.4343 0.02653 0.01701 -0.1320 0.3774 1.0000
8.000 1.4531 0.02729 0.01781 -0.1304 0.3637 1.0000
8.250 1.4745 0.02816 0.01866 -0.1295 0.3507 1.0000
8.500 1.4969 0.02910 0.01957 -0.1288 0.3378 1.0000
8.750 1.5196 0.03007 0.02049 -0.1282 0.3249 1.0000
9.000 1.5314 0.03082 0.02141 -0.1253 0.3123 1.0000
9.250 1.5422 0.03158 0.02231 -0.1223 0.3000 1.0000
9.500 1.5535 0.03230 0.02307 -0.1195 0.2883 1.0000
9.750 1.5617 0.03300 0.02379 -0.1160 0.2764 1.0000
10.000 1.5641 0.03384 0.02478 -0.1116 0.2642 1.0000
10.250 1.5696 0.03478 0.02576 -0.1079 0.2522 1.0000
10.500 1.5771 0.03577 0.02666 -0.1047 0.2400 1.0000
10.750 1.5781 0.03695 0.02802 -0.1005 0.2276 1.0000
11.000 1.5833 0.03825 0.02937 -0.0972 0.2158 1.0000
11.250 1.5919 0.03954 0.03057 -0.0946 0.2052 1.0000
11.500 1.5959 0.04097 0.03214 -0.0913 0.1950 1.0000
11.750 1.6056 0.04246 0.03365 -0.0891 0.1863 1.0000
12.000 1.6138 0.04392 0.03518 -0.0867 0.1785 1.0000
12.250 1.6267 0.04548 0.03676 -0.0850 0.1716 1.0000
12.500 1.6332 0.04710 0.03856 -0.0826 0.1653 1.0000
12.750 1.6502 0.04848 0.03980 -0.0816 0.1587 1.0000
13.000 1.6485 0.05046 0.04212 -0.0783 0.1538 1.0000
13.250 1.6554 0.05209 0.04381 -0.0763 0.1484 1.0000
13.500 1.6666 0.05382 0.04556 -0.0748 0.1430 1.0000
13.750 1.6624 0.05612 0.04816 -0.0718 0.1385 1.0000
14.000 1.6703 0.05773 0.04975 -0.0701 0.1331 1.0000
14.250 1.6698 0.06018 0.05237 -0.0678 0.1283 1.0000
14.500 1.6623 0.06287 0.05530 -0.0652 0.1239 1.0000
14.750 1.6757 0.06447 0.05674 -0.0643 0.1176 1.0000
15.000 1.6580 0.06810 0.06077 -0.0614 0.1143 1.0000
15.250 1.6563 0.07060 0.06334 -0.0598 0.1095 1.0000
15.500 1.6566 0.07342 0.06622 -0.0585 0.1050 1.0000
15.750 1.6403 0.07750 0.07061 -0.0568 0.1019 1.0000
16.000 1.6596 0.07866 0.07154 -0.0563 0.0964 1.0000
16.250 1.6349 0.08377 0.07705 -0.0550 0.0947 1.0000
16.500 1.6165 0.08868 0.08228 -0.0546 0.0925 1.0000
16.750 1.6205 0.09110 0.08469 -0.0542 0.0889 1.0000
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