HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.4 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1606-il-1000000-n5.txt Download as CSV file: xf-hs1606-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-606 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2525 0.09518 0.09359 -0.0411 0.9840 0.0052
-9.500 -0.2461 0.09121 0.08962 -0.0428 0.9766 0.0053
-7.000 -0.2691 0.06738 0.06547 -0.0597 0.8873 0.0028
-6.750 -0.2491 0.06182 0.05985 -0.0672 0.8777 0.0027
-6.500 -0.2235 0.05512 0.05308 -0.0767 0.8701 0.0026
-6.000 -0.1286 0.01515 0.01116 -0.1176 0.8583 0.0023
-5.750 -0.0991 0.01332 0.00895 -0.1185 0.8538 0.0024
-5.500 -0.0700 0.01213 0.00747 -0.1190 0.8495 0.0026
-5.250 -0.0411 0.01138 0.00652 -0.1194 0.8455 0.0028
-5.000 -0.0123 0.01091 0.00593 -0.1197 0.8415 0.0029
-4.750 0.0170 0.00995 0.00477 -0.1202 0.8379 0.0033
-4.250 0.0748 0.00906 0.00369 -0.1207 0.8315 0.0039
-4.000 0.1037 0.00871 0.00326 -0.1210 0.8280 0.0041
-3.750 0.1326 0.00841 0.00288 -0.1212 0.8246 0.0044
-3.500 0.1613 0.00820 0.00262 -0.1214 0.8213 0.0049
-3.250 0.1901 0.00797 0.00234 -0.1215 0.8175 0.0052
-3.000 0.2190 0.00774 0.00203 -0.1217 0.8123 0.0053
-2.750 0.2475 0.00758 0.00177 -0.1217 0.8061 0.0054
-2.500 0.2763 0.00742 0.00155 -0.1218 0.7993 0.0057
-2.000 0.3338 0.00695 0.00118 -0.1222 0.7869 0.0548
-1.750 0.3622 0.00682 0.00110 -0.1224 0.7805 0.0765
-1.500 0.3908 0.00673 0.00104 -0.1225 0.7746 0.0959
-1.250 0.4193 0.00663 0.00102 -0.1227 0.7674 0.1254
-1.000 0.4478 0.00660 0.00100 -0.1228 0.7615 0.1360
-0.750 0.4763 0.00656 0.00098 -0.1229 0.7558 0.1471
-0.500 0.5047 0.00655 0.00097 -0.1230 0.7503 0.1561
-0.250 0.5332 0.00654 0.00097 -0.1231 0.7436 0.1629
0.000 0.5615 0.00654 0.00097 -0.1232 0.7365 0.1700
0.250 0.5898 0.00653 0.00097 -0.1233 0.7280 0.1775
0.500 0.6180 0.00654 0.00099 -0.1233 0.7184 0.1866
0.750 0.6461 0.00656 0.00101 -0.1233 0.7052 0.1953
1.000 0.6737 0.00663 0.00104 -0.1233 0.6841 0.2046
1.250 0.7007 0.00676 0.00109 -0.1231 0.6495 0.2133
1.500 0.7266 0.00705 0.00119 -0.1228 0.5957 0.2222
1.750 0.7527 0.00735 0.00133 -0.1225 0.5503 0.2314
2.000 0.7783 0.00771 0.00150 -0.1222 0.4979 0.2444
2.500 0.8269 0.00877 0.00201 -0.1214 0.3439 0.2942
3.000 0.8737 0.00806 0.00249 -0.1201 0.2778 1.0000
3.250 0.8996 0.00839 0.00267 -0.1199 0.2440 1.0000
3.500 0.9241 0.00891 0.00295 -0.1194 0.1922 1.0000
3.750 0.9480 0.00950 0.00327 -0.1189 0.1374 1.0000
4.000 0.9706 0.01027 0.00371 -0.1182 0.0704 1.0000
4.250 0.9958 0.01067 0.00401 -0.1178 0.0494 1.0000
4.500 1.0215 0.01099 0.00427 -0.1174 0.0395 1.0000
4.750 1.0474 0.01125 0.00454 -0.1172 0.0348 1.0000
5.000 1.0729 0.01156 0.00483 -0.1168 0.0294 1.0000
5.250 1.0987 0.01183 0.00511 -0.1165 0.0267 1.0000
5.500 1.1242 0.01211 0.00540 -0.1161 0.0245 1.0000
5.750 1.1494 0.01244 0.00572 -0.1157 0.0222 1.0000
6.000 1.1742 0.01281 0.00613 -0.1152 0.0197 1.0000
6.250 1.1988 0.01319 0.00655 -0.1147 0.0183 1.0000
6.500 1.2237 0.01350 0.00690 -0.1143 0.0179 1.0000
6.750 1.2483 0.01384 0.00728 -0.1138 0.0171 1.0000
7.000 1.2728 0.01416 0.00762 -0.1133 0.0157 1.0000
7.250 1.2968 0.01452 0.00795 -0.1128 0.0135 1.0000
7.500 1.3198 0.01503 0.00850 -0.1120 0.0115 1.0000
7.750 1.3437 0.01536 0.00888 -0.1115 0.0111 1.0000
8.000 1.3673 0.01573 0.00929 -0.1109 0.0103 1.0000
8.250 1.3903 0.01614 0.00972 -0.1102 0.0090 1.0000
8.500 1.4126 0.01662 0.01018 -0.1094 0.0073 1.0000
8.750 1.4345 0.01711 0.01072 -0.1086 0.0059 1.0000
9.000 1.4545 0.01779 0.01138 -0.1074 0.0034 1.0000
9.250 1.4735 0.01856 0.01220 -0.1061 0.0021 1.0000
9.500 1.4927 0.01928 0.01302 -0.1048 0.0017 1.0000
9.750 1.5105 0.02010 0.01393 -0.1032 0.0014 1.0000
10.000 1.5270 0.02104 0.01498 -0.1015 0.0011 1.0000
10.250 1.5446 0.02179 0.01581 -0.1000 0.0010 1.0000
10.500 1.5612 0.02257 0.01669 -0.0983 0.0009 1.0000
10.750 1.5763 0.02342 0.01764 -0.0964 0.0009 1.0000
11.000 1.5898 0.02432 0.01865 -0.0943 0.0008 1.0000
11.250 1.6008 0.02525 0.01969 -0.0917 0.0008 1.0000
11.500 1.6099 0.02627 0.02082 -0.0889 0.0008 1.0000
11.750 1.6184 0.02738 0.02205 -0.0861 0.0007 1.0000
12.000 1.6263 0.02855 0.02337 -0.0835 0.0007 1.0000
12.250 1.6331 0.02986 0.02480 -0.0808 0.0007 1.0000
12.500 1.6387 0.03129 0.02637 -0.0782 0.0007 1.0000
12.750 1.6435 0.03283 0.02805 -0.0756 0.0006 1.0000
13.000 1.6470 0.03453 0.02989 -0.0732 0.0006 1.0000
13.250 1.6501 0.03633 0.03182 -0.0709 0.0006 1.0000
13.500 1.6512 0.03836 0.03399 -0.0686 0.0006 1.0000
13.750 1.6502 0.04068 0.03647 -0.0665 0.0006 1.0000
14.000 1.6484 0.04316 0.03910 -0.0645 0.0005 1.0000
14.250 1.6446 0.04594 0.04204 -0.0628 0.0005 1.0000
14.500 1.6397 0.04897 0.04522 -0.0614 0.0005 1.0000
14.750 1.6321 0.05242 0.04883 -0.0602 0.0005 1.0000
15.000 1.6227 0.05629 0.05287 -0.0594 0.0005 1.0000
15.250 1.6117 0.06059 0.05732 -0.0591 0.0005 1.0000
15.500 1.5977 0.06558 0.06248 -0.0595 0.0005 1.0000
15.750 1.5827 0.07120 0.06828 -0.0606 0.0005 1.0000
16.000 1.5650 0.07779 0.07504 -0.0628 0.0005 1.0000
16.250 1.5448 0.08537 0.08279 -0.0660 0.0005 1.0000
16.500 1.5209 0.09426 0.09186 -0.0703 0.0005 1.0000
16.750 1.4938 0.10441 0.10218 -0.0756 0.0005 1.0000
17.000 1.4609 0.11621 0.11417 -0.0820 0.0005 1.0000
17.250 1.4237 0.12948 0.12762 -0.0892 0.0005 1.0000
17.500 1.3722 0.14707 0.14540 -0.0990 0.0006 1.0000
17.750 1.2454 0.19029 0.18888 -0.1233 0.0007 1.0000
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Polar data table (+)
Polar graphs
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