HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 100,000 Max Cl/Cd: 67.77 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1708-il-100000.txt Download as CSV file: xf-hs1708-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-708 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 -0.3853 0.10831 0.10389 -0.0193 1.0000 0.0780
-7.500 -0.4034 0.10788 0.10355 -0.0168 1.0000 0.0790
-7.250 -0.4190 0.10733 0.10308 -0.0169 1.0000 0.0799
-7.000 -0.4277 0.10634 0.10214 -0.0215 1.0000 0.0805
-6.750 -0.4262 0.10352 0.09935 -0.0269 1.0000 0.0810
-6.500 -0.4254 0.09858 0.09446 -0.0180 1.0000 0.0823
-6.250 -0.4222 0.09564 0.09153 -0.0153 1.0000 0.0839
-6.000 -0.4189 0.09295 0.08887 -0.0148 1.0000 0.0859
-5.750 -0.4137 0.09011 0.08604 -0.0161 1.0000 0.0886
-5.500 -0.3763 0.08641 0.08212 -0.0381 1.0000 0.0944
-5.250 -0.3789 0.08193 0.07776 -0.0323 1.0000 0.0954
-5.000 -0.3751 0.07891 0.07478 -0.0286 1.0000 0.0970
-4.750 -0.3637 0.07600 0.07185 -0.0286 1.0000 0.1002
-4.500 -0.3163 0.07047 0.06606 -0.0443 1.0000 0.1091
-4.250 -0.3139 0.06784 0.06353 -0.0395 1.0000 0.1119
-4.000 -0.2739 0.06342 0.05890 -0.0489 1.0000 0.1239
-3.750 -0.2631 0.06127 0.05679 -0.0465 1.0000 0.1324
-3.500 -0.2318 0.05733 0.05272 -0.0513 1.0000 0.1427
-3.250 -0.1677 0.05271 0.04769 -0.0637 0.9961 0.1678
-3.000 -0.0775 0.04078 0.03466 -0.0807 0.9942 0.1195
-2.750 -0.0173 0.03550 0.02847 -0.0888 0.9914 0.1207
-2.500 0.0291 0.03334 0.02593 -0.0934 0.9879 0.1268
-2.250 0.0817 0.03155 0.02336 -0.0986 0.9852 0.1368
-2.000 0.1143 0.03101 0.02286 -0.1003 0.9802 0.1456
-1.750 0.1557 0.03030 0.02186 -0.1034 0.9761 0.1570
-1.500 0.2016 0.02983 0.02112 -0.1073 0.9727 0.1707
-1.250 0.2324 0.02956 0.02071 -0.1084 0.9669 0.1843
-1.000 0.2720 0.02928 0.02030 -0.1110 0.9621 0.1995
-0.750 0.3159 0.02926 0.02023 -0.1145 0.9580 0.2218
-0.500 0.3442 0.02912 0.02002 -0.1151 0.9506 0.2393
-0.250 0.3889 0.02895 0.01992 -0.1187 0.9457 0.2655
0.000 0.4239 0.02871 0.01975 -0.1203 0.9358 0.2884
0.250 0.4707 0.02827 0.01942 -0.1238 0.9261 0.3198
0.500 0.5205 0.02769 0.01898 -0.1276 0.9172 0.3595
0.750 0.5535 0.02738 0.01895 -0.1287 0.9073 0.4116
1.000 0.5932 0.02595 0.01868 -0.1302 0.9019 1.0000
1.250 0.6197 0.02624 0.01881 -0.1299 0.8910 1.0000
1.500 0.6557 0.02636 0.01882 -0.1312 0.8824 1.0000
1.750 0.6957 0.02629 0.01868 -0.1331 0.8743 1.0000
2.000 0.7252 0.02642 0.01877 -0.1332 0.8633 1.0000
2.250 0.7751 0.02592 0.01827 -0.1364 0.8579 1.0000
2.500 0.8036 0.02591 0.01828 -0.1361 0.8458 1.0000
2.750 0.8379 0.02568 0.01807 -0.1366 0.8352 1.0000
3.000 0.8874 0.02474 0.01720 -0.1392 0.8296 1.0000
3.250 0.9180 0.02438 0.01690 -0.1388 0.8173 1.0000
3.500 0.9504 0.02389 0.01648 -0.1384 0.8054 1.0000
3.750 0.9856 0.02318 0.01588 -0.1384 0.7943 1.0000
4.000 1.0281 0.02201 0.01479 -0.1392 0.7856 1.0000
4.250 1.0598 0.02124 0.01411 -0.1384 0.7709 1.0000
4.500 1.0845 0.02073 0.01373 -0.1365 0.7512 1.0000
4.750 1.1140 0.01997 0.01306 -0.1353 0.7314 1.0000
5.000 1.1420 0.01928 0.01246 -0.1338 0.7074 1.0000
5.250 1.1679 0.01868 0.01192 -0.1320 0.6755 1.0000
5.500 1.1941 0.01812 0.01128 -0.1302 0.6323 1.0000
5.750 1.2185 0.01798 0.01081 -0.1281 0.5782 1.0000
6.000 1.2392 0.01848 0.01098 -0.1261 0.5275 1.0000
6.250 1.2584 0.01920 0.01149 -0.1242 0.4869 1.0000
6.500 1.2767 0.01995 0.01208 -0.1222 0.4517 1.0000
6.750 1.2937 0.02072 0.01273 -0.1202 0.4183 1.0000
7.000 1.3092 0.02152 0.01344 -0.1179 0.3857 1.0000
7.250 1.3234 0.02237 0.01424 -0.1155 0.3532 1.0000
7.500 1.3338 0.02332 0.01509 -0.1125 0.3152 1.0000
7.750 1.3378 0.02447 0.01607 -0.1085 0.2600 1.0000
8.000 1.3333 0.02637 0.01741 -0.1035 0.1865 1.0000
8.250 1.3313 0.02843 0.01905 -0.0989 0.1487 1.0000
8.500 1.3361 0.03028 0.02073 -0.0954 0.1300 1.0000
8.750 1.3447 0.03204 0.02238 -0.0926 0.1178 1.0000
9.000 1.3562 0.03371 0.02400 -0.0903 0.1078 1.0000
9.250 1.3726 0.03531 0.02568 -0.0886 0.0997 1.0000
9.500 1.4009 0.03746 0.02765 -0.0887 0.0931 1.0000
9.750 1.4238 0.03918 0.02960 -0.0878 0.0877 1.0000
10.000 1.4636 0.04207 0.03233 -0.0902 0.0808 1.0000
10.250 1.4845 0.04416 0.03483 -0.0890 0.0778 1.0000
10.500 1.5076 0.04673 0.03769 -0.0884 0.0748 1.0000
10.750 1.5266 0.04925 0.04036 -0.0874 0.0715 1.0000
11.000 1.5464 0.05344 0.04473 -0.0871 0.0683 1.0000
11.250 1.5468 0.05605 0.04782 -0.0834 0.0671 1.0000
11.500 1.5445 0.05915 0.05137 -0.0796 0.0663 1.0000
11.750 1.5360 0.06227 0.05489 -0.0752 0.0657 1.0000
12.000 1.5233 0.06547 0.05845 -0.0708 0.0651 1.0000
12.250 1.5075 0.06884 0.06217 -0.0666 0.0645 1.0000
12.500 1.4892 0.07250 0.06615 -0.0629 0.0640 1.0000
12.750 1.4683 0.07651 0.07046 -0.0599 0.0636 1.0000
13.000 1.4448 0.08103 0.07527 -0.0576 0.0636 1.0000
13.250 1.4183 0.08619 0.08072 -0.0561 0.0638 1.0000
13.500 1.3895 0.09205 0.08685 -0.0557 0.0643 1.0000
13.750 1.3592 0.09868 0.09371 -0.0565 0.0650 1.0000
14.000 1.3288 0.10608 0.10132 -0.0587 0.0659 1.0000
14.250 1.2997 0.11427 0.10967 -0.0622 0.0669 1.0000
14.500 1.2731 0.12308 0.11861 -0.0666 0.0678 1.0000
14.750 1.2523 0.13210 0.12770 -0.0711 0.0685 1.0000
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Polar data table (+)
Polar graphs
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