HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 1,000,000 Max Cl/Cd: 160.46 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1606-il-1000000.txt Download as CSV file: xf-hs1606-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3547 0.09743 0.09582 -0.0311 1.0000 0.0059
-8.500 -0.3535 0.09497 0.09339 -0.0309 1.0000 0.0060
-8.250 -0.3527 0.09257 0.09102 -0.0308 0.9995 0.0061
-8.000 -0.3368 0.08863 0.08708 -0.0353 0.9966 0.0063
-7.750 -0.3200 0.08455 0.08299 -0.0403 0.9928 0.0065
-7.500 -0.3014 0.08026 0.07870 -0.0460 0.9865 0.0067
-7.250 -0.2803 0.07572 0.07416 -0.0526 0.9791 0.0070
-7.000 -0.2582 0.07101 0.06943 -0.0596 0.9693 0.0073
-6.750 -0.2378 0.06631 0.06470 -0.0660 0.9554 0.0077
-6.500 -0.2156 0.06150 0.05983 -0.0723 0.9412 0.0083
-6.250 -0.1898 0.05719 0.05545 -0.0782 0.9294 0.0088
-6.000 -0.1617 0.05184 0.05002 -0.0855 0.9182 0.0088
-4.750 0.0190 0.01191 0.00739 -0.1215 0.8861 0.0057
-4.500 0.0486 0.01071 0.00595 -0.1218 0.8815 0.0057
-4.250 0.0780 0.00949 0.00452 -0.1223 0.8773 0.0065
-4.000 0.1071 0.00901 0.00395 -0.1225 0.8730 0.0072
-3.750 0.1362 0.00857 0.00340 -0.1228 0.8689 0.0076
-3.500 0.1651 0.00822 0.00296 -0.1229 0.8648 0.0080
-3.250 0.1938 0.00801 0.00268 -0.1230 0.8605 0.0087
-3.000 0.2227 0.00771 0.00231 -0.1231 0.8551 0.0089
-2.750 0.2514 0.00746 0.00191 -0.1231 0.8494 0.0092
-2.500 0.2802 0.00729 0.00165 -0.1232 0.8435 0.0103
-2.250 0.3091 0.00688 0.00142 -0.1234 0.8378 0.0596
-2.000 0.3376 0.00670 0.00134 -0.1236 0.8325 0.0976
-1.750 0.3661 0.00660 0.00130 -0.1237 0.8272 0.1215
-1.500 0.3945 0.00655 0.00127 -0.1238 0.8223 0.1406
-1.250 0.4229 0.00651 0.00128 -0.1239 0.8169 0.1587
-1.000 0.4514 0.00648 0.00125 -0.1240 0.8119 0.1677
-0.750 0.4797 0.00649 0.00123 -0.1240 0.8077 0.1767
-0.500 0.5083 0.00645 0.00123 -0.1241 0.8033 0.1857
-0.250 0.5367 0.00643 0.00122 -0.1242 0.7984 0.1928
0.000 0.5650 0.00643 0.00122 -0.1243 0.7937 0.2012
0.250 0.5935 0.00640 0.00122 -0.1244 0.7886 0.2097
0.500 0.6219 0.00639 0.00123 -0.1245 0.7830 0.2190
0.750 0.6501 0.00638 0.00124 -0.1245 0.7771 0.2305
1.000 0.6784 0.00634 0.00126 -0.1246 0.7696 0.2438
1.250 0.7066 0.00633 0.00129 -0.1247 0.7623 0.2604
1.500 0.7349 0.00625 0.00133 -0.1248 0.7538 0.2969
1.750 0.7575 0.00485 0.00147 -0.1240 0.7455 1.0000
2.000 0.7852 0.00492 0.00149 -0.1239 0.7303 1.0000
2.250 0.8119 0.00506 0.00149 -0.1235 0.6960 1.0000
2.500 0.8371 0.00538 0.00158 -0.1230 0.6317 1.0000
2.750 0.8598 0.00609 0.00183 -0.1221 0.5338 1.0000
3.000 0.8842 0.00664 0.00207 -0.1216 0.4655 1.0000
3.250 0.9083 0.00721 0.00232 -0.1210 0.3957 1.0000
3.500 0.9329 0.00772 0.00259 -0.1206 0.3424 1.0000
3.750 0.9582 0.00813 0.00283 -0.1202 0.3034 1.0000
4.000 0.9830 0.00858 0.00308 -0.1198 0.2572 1.0000
4.250 1.0063 0.00922 0.00341 -0.1192 0.1948 1.0000
4.500 1.0266 0.01027 0.00398 -0.1182 0.0993 1.0000
4.750 1.0489 0.01105 0.00449 -0.1173 0.0499 1.0000
5.000 1.0737 0.01149 0.00489 -0.1168 0.0385 1.0000
5.250 1.0992 0.01180 0.00520 -0.1164 0.0344 1.0000
5.500 1.1233 0.01232 0.00573 -0.1157 0.0289 1.0000
5.750 1.1481 0.01270 0.00617 -0.1152 0.0273 1.0000
6.000 1.1733 0.01302 0.00653 -0.1148 0.0260 1.0000
6.250 1.1978 0.01340 0.00696 -0.1143 0.0242 1.0000
6.500 1.2218 0.01385 0.00744 -0.1136 0.0226 1.0000
6.750 1.2448 0.01442 0.00806 -0.1128 0.0211 1.0000
7.000 1.2622 0.01569 0.00947 -0.1109 0.0185 1.0000
7.250 1.2903 0.01550 0.00924 -0.1112 0.0178 1.0000
7.500 1.3153 0.01570 0.00948 -0.1108 0.0168 1.0000
7.750 1.3394 0.01601 0.00981 -0.1103 0.0155 1.0000
8.000 1.3632 0.01633 0.01014 -0.1098 0.0143 1.0000
8.250 1.3852 0.01686 0.01068 -0.1089 0.0127 1.0000
8.500 1.4046 0.01767 0.01158 -0.1076 0.0114 1.0000
8.750 1.4311 0.01760 0.01149 -0.1076 0.0105 1.0000
9.000 1.4553 0.01778 0.01155 -0.1073 0.0069 1.0000
9.250 1.4741 0.01859 0.01235 -0.1059 0.0037 1.0000
9.500 1.4923 0.01942 0.01327 -0.1044 0.0029 1.0000
9.750 1.5074 0.02059 0.01457 -0.1024 0.0023 1.0000
10.000 1.5235 0.02157 0.01567 -0.1005 0.0021 1.0000
10.250 1.5393 0.02250 0.01672 -0.0987 0.0021 1.0000
10.500 1.5533 0.02353 0.01787 -0.0966 0.0020 1.0000
10.750 1.5653 0.02463 0.01911 -0.0942 0.0019 1.0000
11.000 1.5746 0.02576 0.02038 -0.0913 0.0018 1.0000
11.250 1.5817 0.02694 0.02169 -0.0881 0.0018 1.0000
11.500 1.5877 0.02826 0.02316 -0.0850 0.0017 1.0000
11.750 1.5926 0.02971 0.02476 -0.0819 0.0017 1.0000
12.000 1.5970 0.03125 0.02644 -0.0790 0.0016 1.0000
12.250 1.6003 0.03291 0.02827 -0.0762 0.0015 1.0000
12.500 1.6020 0.03478 0.03030 -0.0734 0.0015 1.0000
12.750 1.6025 0.03681 0.03248 -0.0709 0.0015 1.0000
13.000 1.6017 0.03905 0.03488 -0.0684 0.0014 1.0000
13.250 1.6002 0.04143 0.03741 -0.0663 0.0014 1.0000
13.500 1.5954 0.04426 0.04041 -0.0642 0.0013 1.0000
13.750 1.5873 0.04759 0.04392 -0.0624 0.0013 1.0000
14.000 1.5781 0.05122 0.04774 -0.0610 0.0013 1.0000
14.250 1.5655 0.05545 0.05215 -0.0601 0.0013 1.0000
14.500 1.5504 0.06032 0.05720 -0.0598 0.0012 1.0000
14.750 1.5339 0.06575 0.06282 -0.0603 0.0012 1.0000
15.000 1.5160 0.07197 0.06922 -0.0618 0.0012 1.0000
15.250 1.4948 0.07949 0.07692 -0.0646 0.0012 1.0000
15.500 1.4771 0.08697 0.08457 -0.0680 0.0012 1.0000
15.750 1.4553 0.09589 0.09367 -0.0726 0.0012 1.0000
16.000 1.4328 0.10547 0.10340 -0.0777 0.0012 1.0000
16.250 1.4080 0.11580 0.11388 -0.0832 0.0013 1.0000
16.500 1.3791 0.12733 0.12556 -0.0893 0.0013 1.0000
16.750 1.3440 0.14091 0.13930 -0.0966 0.0014 1.0000
17.000 1.2954 0.15912 0.15769 -0.1065 0.0015 1.0000
17.250 1.1404 0.22658 0.22525 -0.1425 0.0023 1.0000
17.500 1.1428 0.23350 0.23216 -0.1460 0.0023 1.0000
17.750 1.1464 0.23984 0.23849 -0.1494 0.0023 1.0000
18.000 1.1502 0.24636 0.24499 -0.1529 0.0023 1.0000
18.250 0.8285 0.21562 0.21436 -0.1039 0.0034 1.0000
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Polar data table (+)
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