HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 500,000 Max Cl/Cd: 95.61 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3510-il-500000-n5.txt Download as CSV file: xf-hq3510-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3390 0.11139 0.10906 -0.0386 1.0000 0.0086
-10.250 -0.3368 0.10803 0.10573 -0.0393 1.0000 0.0086
-10.000 -0.3358 0.10465 0.10238 -0.0398 1.0000 0.0086
-9.500 -0.2180 0.08192 0.07980 -0.0538 0.9815 0.0078
-9.250 -0.2129 0.07729 0.07517 -0.0563 0.9779 0.0074
-9.000 -0.2078 0.07232 0.07021 -0.0593 0.9745 0.0070
-8.750 -0.2049 0.06688 0.06477 -0.0625 0.9696 0.0067
-8.500 -0.2034 0.06083 0.05872 -0.0664 0.9634 0.0064
-8.250 -0.2112 0.05204 0.04995 -0.0721 0.9548 0.0058
-8.000 -0.2112 0.04618 0.04409 -0.0770 0.9434 0.0059
-7.750 -0.2672 0.05513 0.05293 -0.0889 0.9490 0.0054
-7.250 -0.2528 0.03921 0.03650 -0.1034 0.9200 0.0053
-7.000 -0.2587 0.02538 0.02173 -0.1062 0.9057 0.0054
-6.750 -0.2441 0.02034 0.01599 -0.1065 0.8974 0.0058
-6.500 -0.2207 0.01865 0.01400 -0.1065 0.8914 0.0061
-6.250 -0.1964 0.01720 0.01229 -0.1064 0.8853 0.0064
-6.000 -0.1713 0.01603 0.01087 -0.1062 0.8794 0.0067
-5.750 -0.1453 0.01520 0.00985 -0.1061 0.8740 0.0073
-5.500 -0.1193 0.01432 0.00879 -0.1060 0.8680 0.0078
-5.250 -0.0931 0.01341 0.00765 -0.1057 0.8628 0.0081
-5.000 -0.0669 0.01256 0.00664 -0.1055 0.8570 0.0083
-4.750 -0.0403 0.01189 0.00583 -0.1053 0.8514 0.0085
-4.500 -0.0141 0.01106 0.00486 -0.1051 0.8462 0.0090
-4.250 0.0127 0.01051 0.00422 -0.1050 0.8402 0.0096
-4.000 0.0400 0.01014 0.00376 -0.1049 0.8350 0.0102
-3.750 0.0674 0.00985 0.00340 -0.1048 0.8292 0.0111
-3.500 0.0950 0.00960 0.00308 -0.1048 0.8235 0.0122
-3.250 0.1227 0.00937 0.00277 -0.1047 0.8180 0.0129
-3.000 0.1505 0.00915 0.00250 -0.1047 0.8117 0.0146
-2.750 0.1782 0.00893 0.00229 -0.1046 0.8060 0.0245
-2.500 0.2059 0.00877 0.00213 -0.1046 0.7989 0.0368
-2.250 0.2335 0.00865 0.00198 -0.1046 0.7916 0.0462
-2.000 0.2610 0.00852 0.00185 -0.1045 0.7820 0.0613
-1.750 0.2883 0.00841 0.00173 -0.1044 0.7712 0.0776
-1.250 0.3421 0.00772 0.00148 -0.1045 0.7503 0.2655
-1.000 0.3680 0.00705 0.00144 -0.1046 0.7404 0.4873
-0.750 0.3949 0.00690 0.00146 -0.1044 0.7307 0.5628
-0.500 0.4216 0.00684 0.00149 -0.1041 0.7201 0.6188
-0.250 0.4481 0.00682 0.00155 -0.1037 0.7094 0.6664
0.000 0.4749 0.00683 0.00158 -0.1034 0.6981 0.6948
0.250 0.5019 0.00689 0.00158 -0.1032 0.6847 0.7048
0.500 0.5290 0.00694 0.00159 -0.1030 0.6717 0.7125
1.000 0.5833 0.00706 0.00164 -0.1027 0.6487 0.7294
1.250 0.6101 0.00714 0.00168 -0.1024 0.6345 0.7380
1.500 0.6367 0.00723 0.00173 -0.1022 0.6188 0.7473
1.750 0.6631 0.00733 0.00179 -0.1019 0.6025 0.7566
2.000 0.6891 0.00745 0.00187 -0.1015 0.5839 0.7666
2.500 0.7395 0.00778 0.00206 -0.1005 0.5336 0.7889
2.750 0.7639 0.00799 0.00219 -0.0998 0.5045 0.8013
3.000 0.7874 0.00825 0.00236 -0.0991 0.4713 0.8151
3.250 0.8107 0.00853 0.00254 -0.0983 0.4378 0.8316
3.500 0.8333 0.00878 0.00273 -0.0973 0.4062 0.8533
3.750 0.8538 0.00897 0.00292 -0.0958 0.3738 0.9020
4.000 0.8835 0.00930 0.00316 -0.0966 0.3375 1.0000
4.250 0.9074 0.00969 0.00340 -0.0960 0.3079 1.0000
4.500 0.9317 0.01004 0.00365 -0.0956 0.2879 1.0000
4.750 0.9563 0.01035 0.00389 -0.0951 0.2727 1.0000
5.000 0.9810 0.01065 0.00415 -0.0947 0.2603 1.0000
5.250 1.0057 0.01094 0.00443 -0.0943 0.2487 1.0000
5.500 1.0301 0.01125 0.00470 -0.0938 0.2357 1.0000
5.750 1.0537 0.01161 0.00499 -0.0933 0.2187 1.0000
6.000 1.0772 0.01198 0.00527 -0.0927 0.1972 1.0000
6.250 1.1000 0.01239 0.00561 -0.0920 0.1763 1.0000
6.500 1.1224 0.01283 0.00595 -0.0913 0.1535 1.0000
6.750 1.1435 0.01337 0.00637 -0.0904 0.1275 1.0000
7.000 1.1611 0.01420 0.00695 -0.0890 0.0893 1.0000
7.250 1.1770 0.01518 0.00767 -0.0873 0.0516 1.0000
7.500 1.1920 0.01622 0.00850 -0.0855 0.0201 1.0000
7.750 1.2083 0.01713 0.00935 -0.0838 0.0054 1.0000
8.000 1.2280 0.01769 0.00996 -0.0826 0.0045 1.0000
8.250 1.2471 0.01828 0.01061 -0.0813 0.0041 1.0000
8.500 1.2652 0.01889 0.01131 -0.0799 0.0037 1.0000
8.750 1.2811 0.01956 0.01208 -0.0781 0.0034 1.0000
9.000 1.2951 0.02034 0.01297 -0.0759 0.0032 1.0000
9.250 1.3089 0.02111 0.01383 -0.0739 0.0032 1.0000
9.500 1.3218 0.02194 0.01476 -0.0718 0.0031 1.0000
9.750 1.3338 0.02283 0.01575 -0.0696 0.0030 1.0000
10.000 1.3451 0.02377 0.01682 -0.0675 0.0029 1.0000
10.250 1.3559 0.02475 0.01789 -0.0654 0.0027 1.0000
10.500 1.3650 0.02586 0.01911 -0.0632 0.0026 1.0000
10.750 1.3731 0.02709 0.02044 -0.0611 0.0025 1.0000
11.000 1.3800 0.02843 0.02189 -0.0590 0.0023 1.0000
11.250 1.3854 0.02993 0.02351 -0.0568 0.0023 1.0000
11.500 1.3902 0.03153 0.02522 -0.0549 0.0022 1.0000
11.750 1.3933 0.03335 0.02715 -0.0530 0.0022 1.0000
12.000 1.3953 0.03533 0.02926 -0.0512 0.0021 1.0000
12.250 1.3965 0.03747 0.03152 -0.0496 0.0020 1.0000
12.500 1.3962 0.03986 0.03403 -0.0482 0.0020 1.0000
12.750 1.3947 0.04249 0.03679 -0.0470 0.0020 1.0000
13.000 1.3896 0.04564 0.04007 -0.0461 0.0019 1.0000
13.250 1.3843 0.04899 0.04359 -0.0454 0.0018 1.0000
13.500 1.3779 0.05265 0.04739 -0.0451 0.0018 1.0000
13.750 1.3714 0.05651 0.05140 -0.0452 0.0018 1.0000
14.000 1.3632 0.06084 0.05588 -0.0456 0.0018 1.0000
14.250 1.3539 0.06558 0.06077 -0.0465 0.0017 1.0000
14.500 1.3354 0.07195 0.06734 -0.0479 0.0017 1.0000
14.750 1.3278 0.07700 0.07254 -0.0496 0.0017 1.0000
15.000 1.3193 0.08245 0.07815 -0.0517 0.0017 1.0000
15.250 1.3099 0.08826 0.08411 -0.0541 0.0017 1.0000
15.500 1.3028 0.09403 0.09004 -0.0569 0.0016 1.0000
15.750 1.2925 0.10050 0.09667 -0.0601 0.0016 1.0000
16.000 1.2814 0.10727 0.10359 -0.0635 0.0016 1.0000
16.250 1.2716 0.11411 0.11057 -0.0672 0.0016 1.0000
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