HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 200,000 Max Cl/Cd: 84.17 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq358-il-200000-n5.txt Download as CSV file: xf-hq358-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3387 0.09357 0.09020 -0.0328 1.0000 0.0167
-7.750 -0.3438 0.09153 0.08823 -0.0316 1.0000 0.0167
-7.500 -0.3540 0.08998 0.08676 -0.0296 1.0000 0.0170
-7.250 -0.3405 0.08655 0.08336 -0.0369 0.9934 0.0180
-5.750 -0.1852 0.05527 0.05167 -0.0838 0.9614 0.0185
-4.750 -0.0793 0.03245 0.02783 -0.0999 0.9395 0.0106
-4.500 -0.0508 0.03093 0.02616 -0.1026 0.9360 0.0145
-4.250 -0.0203 0.02719 0.02200 -0.1040 0.9309 0.0139
-4.000 0.0110 0.02350 0.01781 -0.1049 0.9259 0.0128
-3.750 0.0448 0.02025 0.01400 -0.1059 0.9226 0.0122
-3.500 0.0748 0.01806 0.01135 -0.1060 0.9179 0.0121
-3.250 0.1040 0.01639 0.00937 -0.1060 0.9128 0.0123
-3.000 0.1351 0.01504 0.00780 -0.1064 0.9091 0.0130
-2.750 0.1631 0.01423 0.00688 -0.1063 0.9038 0.0154
-2.500 0.1917 0.01350 0.00604 -0.1063 0.8984 0.0176
-2.250 0.2223 0.01270 0.00509 -0.1067 0.8944 0.0183
-2.000 0.2492 0.01212 0.00439 -0.1065 0.8877 0.0203
-1.750 0.2789 0.01173 0.00387 -0.1067 0.8826 0.0281
-1.500 0.3070 0.01140 0.00358 -0.1067 0.8765 0.0627
-1.250 0.3340 0.01024 0.00339 -0.1074 0.8703 0.3634
-0.750 0.3798 0.00930 0.00358 -0.1046 0.8554 0.7567
-0.500 0.4024 0.00912 0.00344 -0.1030 0.8451 0.8074
-0.250 0.4266 0.00895 0.00327 -0.1017 0.8346 0.8424
0.000 0.4532 0.00881 0.00309 -0.1011 0.8240 0.8673
0.250 0.4827 0.00864 0.00291 -0.1010 0.8134 0.9114
0.500 0.5164 0.00858 0.00278 -0.1022 0.8014 1.0000
0.750 0.5441 0.00862 0.00271 -0.1021 0.7886 1.0000
1.000 0.5718 0.00866 0.00266 -0.1020 0.7759 1.0000
1.250 0.5994 0.00873 0.00265 -0.1019 0.7639 1.0000
1.500 0.6269 0.00880 0.00268 -0.1018 0.7517 1.0000
1.750 0.6542 0.00888 0.00269 -0.1016 0.7384 1.0000
2.000 0.6813 0.00897 0.00273 -0.1014 0.7239 1.0000
2.250 0.7082 0.00908 0.00277 -0.1012 0.7082 1.0000
2.500 0.7349 0.00920 0.00283 -0.1009 0.6906 1.0000
2.750 0.7612 0.00934 0.00296 -0.1005 0.6704 1.0000
3.000 0.7872 0.00951 0.00306 -0.1001 0.6482 1.0000
3.250 0.8127 0.00971 0.00318 -0.0995 0.6215 1.0000
3.500 0.8375 0.00995 0.00333 -0.0989 0.5891 1.0000
3.750 0.8613 0.01027 0.00350 -0.0981 0.5503 1.0000
4.000 0.8839 0.01069 0.00378 -0.0971 0.5043 1.0000
4.250 0.9056 0.01121 0.00408 -0.0960 0.4555 1.0000
4.500 0.9271 0.01175 0.00444 -0.0950 0.4108 1.0000
4.750 0.9492 0.01229 0.00483 -0.0941 0.3725 1.0000
5.000 0.9715 0.01281 0.00525 -0.0932 0.3391 1.0000
5.250 0.9935 0.01337 0.00576 -0.0924 0.3067 1.0000
5.500 1.0130 0.01416 0.00628 -0.0913 0.2599 1.0000
5.750 1.0345 0.01477 0.00678 -0.0904 0.2287 1.0000
6.000 1.0579 0.01522 0.00727 -0.0898 0.2085 1.0000
6.250 1.0787 0.01592 0.00782 -0.0889 0.1646 1.0000
6.500 1.0938 0.01730 0.00867 -0.0873 0.0860 1.0000
6.750 1.1048 0.01931 0.01009 -0.0852 0.0130 1.0000
7.000 1.1240 0.02032 0.01117 -0.0838 0.0076 1.0000
7.250 1.1438 0.02120 0.01230 -0.0825 0.0066 1.0000
7.500 1.1626 0.02218 0.01348 -0.0811 0.0060 1.0000
7.750 1.1798 0.02329 0.01478 -0.0795 0.0056 1.0000
8.000 1.1950 0.02456 0.01624 -0.0776 0.0053 1.0000
8.250 1.2081 0.02597 0.01783 -0.0756 0.0051 1.0000
8.500 1.2191 0.02754 0.01957 -0.0732 0.0050 1.0000
8.750 1.2286 0.02924 0.02143 -0.0707 0.0049 1.0000
9.000 1.2364 0.03111 0.02346 -0.0680 0.0048 1.0000
9.250 1.2447 0.03313 0.02566 -0.0655 0.0048 1.0000
9.500 1.2533 0.03533 0.02805 -0.0632 0.0047 1.0000
9.750 1.2615 0.03776 0.03070 -0.0609 0.0047 1.0000
10.000 1.2681 0.04039 0.03358 -0.0586 0.0047 1.0000
10.250 1.2703 0.04347 0.03694 -0.0562 0.0046 1.0000
10.750 1.2619 0.04974 0.04392 -0.0511 0.0042 1.0000
11.000 1.2570 0.05269 0.04715 -0.0491 0.0041 1.0000
11.250 1.2520 0.05556 0.05031 -0.0477 0.0039 1.0000
11.500 1.2431 0.05924 0.05425 -0.0467 0.0037 1.0000
11.750 1.2320 0.06339 0.05867 -0.0463 0.0036 1.0000
12.000 1.2189 0.06812 0.06365 -0.0467 0.0036 1.0000
12.250 1.2043 0.07344 0.06920 -0.0480 0.0035 1.0000
12.500 1.1887 0.07940 0.07538 -0.0502 0.0035 1.0000
12.750 1.1721 0.08611 0.08229 -0.0535 0.0036 1.0000
13.000 1.1551 0.09360 0.08998 -0.0577 0.0036 1.0000
13.250 1.1380 0.10195 0.09851 -0.0629 0.0037 1.0000
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Polar data table (+)
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