HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 500,000 Max Cl/Cd: 121.94 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1606-il-500000-n5.txt Download as CSV file: xf-hs1606-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3743 0.11537 0.11297 -0.0256 1.0000 0.0080
-9.750 -0.3685 0.11202 0.10964 -0.0270 1.0000 0.0083
-9.500 -0.3632 0.10871 0.10635 -0.0287 1.0000 0.0086
-7.000 -0.2630 0.06941 0.06712 -0.0604 0.9478 0.0050
-6.750 -0.2425 0.06449 0.06217 -0.0672 0.9366 0.0048
-6.500 -0.2194 0.05914 0.05676 -0.0746 0.9256 0.0046
-6.250 -0.1921 0.05283 0.05036 -0.0834 0.9150 0.0044
-6.000 -0.1289 0.02216 0.01852 -0.1161 0.9055 0.0037
-5.750 -0.0971 0.01783 0.01347 -0.1190 0.8998 0.0038
-5.500 -0.0676 0.01572 0.01090 -0.1201 0.8941 0.0039
-5.250 -0.0384 0.01428 0.00910 -0.1207 0.8893 0.0042
-5.000 -0.0093 0.01318 0.00774 -0.1212 0.8843 0.0046
-4.750 0.0195 0.01237 0.00670 -0.1214 0.8794 0.0050
-4.500 0.0483 0.01172 0.00588 -0.1216 0.8752 0.0052
-4.250 0.0773 0.01096 0.00497 -0.1220 0.8706 0.0059
-4.000 0.1060 0.01046 0.00436 -0.1223 0.8665 0.0069
-3.750 0.1348 0.01004 0.00381 -0.1225 0.8630 0.0072
-3.500 0.1638 0.00966 0.00332 -0.1226 0.8593 0.0074
-3.250 0.1927 0.00936 0.00291 -0.1228 0.8552 0.0076
-3.000 0.2214 0.00913 0.00257 -0.1229 0.8516 0.0081
-2.750 0.2502 0.00895 0.00228 -0.1229 0.8487 0.0090
-2.500 0.2791 0.00850 0.00200 -0.1232 0.8446 0.0501
-2.250 0.3075 0.00831 0.00188 -0.1234 0.8395 0.0761
-2.000 0.3355 0.00817 0.00180 -0.1234 0.8335 0.1028
-1.750 0.3636 0.00808 0.00175 -0.1234 0.8257 0.1271
-1.500 0.3916 0.00804 0.00168 -0.1234 0.8186 0.1382
-1.250 0.4197 0.00800 0.00163 -0.1234 0.8115 0.1497
-1.000 0.4478 0.00798 0.00160 -0.1234 0.8055 0.1608
-0.750 0.4760 0.00794 0.00157 -0.1234 0.7984 0.1690
-0.500 0.5040 0.00794 0.00153 -0.1233 0.7918 0.1772
-0.250 0.5323 0.00791 0.00154 -0.1234 0.7852 0.1866
0.000 0.5604 0.00790 0.00153 -0.1234 0.7800 0.1954
0.250 0.5887 0.00789 0.00155 -0.1235 0.7741 0.2051
0.500 0.6168 0.00787 0.00156 -0.1235 0.7673 0.2157
0.750 0.6449 0.00786 0.00159 -0.1235 0.7602 0.2258
1.000 0.6728 0.00785 0.00161 -0.1235 0.7522 0.2370
1.250 0.7008 0.00784 0.00166 -0.1235 0.7426 0.2495
1.500 0.7286 0.00782 0.00171 -0.1235 0.7309 0.2695
1.750 0.7563 0.00777 0.00176 -0.1235 0.7155 0.3120
2.000 0.7768 0.00645 0.00186 -0.1220 0.6977 1.0000
2.250 0.8036 0.00659 0.00191 -0.1217 0.6705 1.0000
2.500 0.8274 0.00700 0.00202 -0.1208 0.6005 1.0000
2.750 0.8479 0.00786 0.00233 -0.1195 0.4961 1.0000
3.000 0.8706 0.00856 0.00264 -0.1187 0.4162 1.0000
3.250 0.8942 0.00915 0.00293 -0.1181 0.3569 1.0000
3.500 0.9181 0.00969 0.00325 -0.1176 0.3080 1.0000
3.750 0.9429 0.01012 0.00352 -0.1172 0.2703 1.0000
4.000 0.9667 0.01068 0.00383 -0.1166 0.2184 1.0000
4.250 0.9893 0.01137 0.00423 -0.1159 0.1590 1.0000
4.500 1.0096 0.01239 0.00482 -0.1149 0.0784 1.0000
4.750 1.0329 0.01300 0.00530 -0.1142 0.0506 1.0000
5.000 1.0575 0.01341 0.00569 -0.1137 0.0416 1.0000
5.250 1.0824 0.01378 0.00608 -0.1132 0.0364 1.0000
5.500 1.1068 0.01419 0.00651 -0.1126 0.0324 1.0000
5.750 1.1303 0.01473 0.00707 -0.1119 0.0280 1.0000
6.000 1.1548 0.01510 0.00751 -0.1114 0.0265 1.0000
6.250 1.1787 0.01552 0.00799 -0.1107 0.0247 1.0000
6.500 1.2022 0.01599 0.00852 -0.1100 0.0230 1.0000
6.750 1.2249 0.01653 0.00911 -0.1092 0.0214 1.0000
7.000 1.2463 0.01724 0.00987 -0.1082 0.0198 1.0000
7.250 1.2650 0.01824 0.01098 -0.1066 0.0184 1.0000
7.500 1.2870 0.01878 0.01161 -0.1057 0.0180 1.0000
7.750 1.3096 0.01921 0.01215 -0.1049 0.0171 1.0000
8.000 1.3324 0.01960 0.01259 -0.1043 0.0155 1.0000
8.250 1.3558 0.01987 0.01286 -0.1037 0.0136 1.0000
8.500 1.3752 0.02060 0.01361 -0.1025 0.0115 1.0000
8.750 1.3975 0.02096 0.01404 -0.1018 0.0106 1.0000
9.000 1.4181 0.02147 0.01464 -0.1008 0.0093 1.0000
9.250 1.4385 0.02198 0.01517 -0.0998 0.0077 1.0000
9.500 1.4568 0.02270 0.01594 -0.0984 0.0062 1.0000
9.750 1.4737 0.02350 0.01682 -0.0968 0.0044 1.0000
10.000 1.4880 0.02453 0.01795 -0.0948 0.0034 1.0000
10.250 1.5008 0.02561 0.01914 -0.0926 0.0029 1.0000
10.500 1.5103 0.02682 0.02047 -0.0898 0.0025 1.0000
10.750 1.5166 0.02828 0.02210 -0.0866 0.0022 1.0000
11.000 1.5244 0.02960 0.02359 -0.0838 0.0021 1.0000
11.250 1.5312 0.03102 0.02518 -0.0810 0.0020 1.0000
11.500 1.5370 0.03256 0.02690 -0.0783 0.0019 1.0000
11.750 1.5417 0.03422 0.02874 -0.0757 0.0018 1.0000
12.000 1.5457 0.03598 0.03067 -0.0732 0.0017 1.0000
12.250 1.5488 0.03785 0.03272 -0.0708 0.0016 1.0000
12.500 1.5505 0.03993 0.03497 -0.0685 0.0015 1.0000
12.750 1.5510 0.04216 0.03741 -0.0665 0.0014 1.0000
13.000 1.5498 0.04466 0.04009 -0.0645 0.0014 1.0000
13.250 1.5469 0.04741 0.04301 -0.0628 0.0013 1.0000
13.500 1.5407 0.05066 0.04646 -0.0612 0.0012 1.0000
13.750 1.5310 0.05445 0.05046 -0.0600 0.0012 1.0000
14.000 1.5200 0.05862 0.05483 -0.0593 0.0012 1.0000
14.250 1.5057 0.06350 0.05992 -0.0593 0.0011 1.0000
14.500 1.4899 0.06896 0.06558 -0.0600 0.0011 1.0000
14.750 1.4727 0.07521 0.07203 -0.0617 0.0011 1.0000
15.000 1.4540 0.08234 0.07936 -0.0645 0.0011 1.0000
15.250 1.4332 0.09056 0.08778 -0.0684 0.0011 1.0000
15.500 1.4125 0.09942 0.09683 -0.0731 0.0012 1.0000
15.750 1.3886 0.10954 0.10713 -0.0787 0.0012 1.0000
16.000 1.3615 0.12078 0.11855 -0.0849 0.0012 1.0000
16.250 1.3276 0.13426 0.13221 -0.0923 0.0013 1.0000
16.500 1.2632 0.15747 0.15562 -0.1049 0.0016 1.0000
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Polar data table (+)
Polar graphs
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