HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 200,000 Max Cl/Cd: 86.11 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq308-il-200000.txt Download as CSV file: xf-hq308-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3839 0.08982 0.08658 -0.0363 1.0000 0.0290
-7.500 -0.3900 0.08726 0.08409 -0.0367 1.0000 0.0291
-7.250 -0.3949 0.08445 0.08134 -0.0378 1.0000 0.0291
-7.000 -0.3997 0.08158 0.07850 -0.0387 1.0000 0.0291
-6.750 -0.4038 0.07878 0.07569 -0.0390 1.0000 0.0292
-6.500 -0.4061 0.07589 0.07277 -0.0393 1.0000 0.0292
-6.250 -0.4155 0.07003 0.06695 -0.0396 1.0000 0.0298
-6.000 -0.4186 0.06659 0.06357 -0.0375 1.0000 0.0306
-5.750 -0.4174 0.06397 0.06098 -0.0361 1.0000 0.0314
-5.500 -0.3947 0.05982 0.05672 -0.0404 0.9971 0.0330
-5.250 -0.3611 0.05465 0.05139 -0.0475 0.9930 0.0357
-5.000 -0.3097 0.05046 0.04656 -0.0567 0.9875 0.0414
-4.750 -0.2799 0.04315 0.03901 -0.0624 0.9840 0.0431
-4.500 -0.2520 0.04027 0.03621 -0.0652 0.9809 0.0504
-4.250 -0.2163 0.03602 0.03145 -0.0691 0.9755 0.0572
-4.000 -0.1823 0.03310 0.02840 -0.0719 0.9720 0.0622
-3.750 -0.1423 0.02994 0.02482 -0.0756 0.9694 0.0719
-3.500 -0.1104 0.02784 0.02236 -0.0772 0.9641 0.0843
-3.250 -0.0672 0.02237 0.01605 -0.0769 0.9616 0.0356
-3.000 -0.0270 0.02042 0.01350 -0.0778 0.9586 0.0288
-2.750 0.0115 0.01814 0.01092 -0.0796 0.9565 0.0284
-2.250 0.0773 0.01543 0.00806 -0.0814 0.9474 0.0373
-2.000 0.1159 0.01429 0.00689 -0.0834 0.9443 0.0486
-1.750 0.1514 0.01169 0.00618 -0.0861 0.9422 0.5471
-1.500 0.1730 0.01139 0.00634 -0.0841 0.9345 0.7288
-1.250 0.2083 0.01121 0.00619 -0.0850 0.9307 0.7876
-1.000 0.2357 0.01097 0.00605 -0.0840 0.9248 0.8486
-0.750 0.2732 0.01053 0.00576 -0.0848 0.9202 0.9477
-0.500 0.3239 0.01030 0.00538 -0.0896 0.9169 1.0000
-0.250 0.3569 0.01026 0.00521 -0.0908 0.9094 1.0000
0.000 0.3929 0.01016 0.00500 -0.0924 0.9037 1.0000
0.250 0.4236 0.01011 0.00487 -0.0929 0.8953 1.0000
0.500 0.4584 0.00990 0.00457 -0.0938 0.8883 1.0000
0.750 0.4858 0.00985 0.00445 -0.0935 0.8775 1.0000
1.000 0.5138 0.00981 0.00437 -0.0933 0.8680 1.0000
1.250 0.5437 0.00973 0.00424 -0.0933 0.8601 1.0000
1.500 0.5707 0.00971 0.00420 -0.0928 0.8493 1.0000
1.750 0.5973 0.00965 0.00411 -0.0922 0.8370 1.0000
2.000 0.6240 0.00959 0.00401 -0.0915 0.8237 1.0000
2.250 0.6506 0.00956 0.00396 -0.0908 0.8105 1.0000
2.500 0.6772 0.00955 0.00395 -0.0903 0.7971 1.0000
2.750 0.7037 0.00956 0.00398 -0.0897 0.7828 1.0000
3.000 0.7303 0.00956 0.00398 -0.0891 0.7675 1.0000
3.250 0.7561 0.00960 0.00402 -0.0884 0.7491 1.0000
3.500 0.7820 0.00965 0.00406 -0.0876 0.7290 1.0000
3.750 0.8075 0.00972 0.00413 -0.0868 0.7056 1.0000
4.000 0.8326 0.00983 0.00426 -0.0860 0.6787 1.0000
4.250 0.8572 0.01000 0.00438 -0.0850 0.6472 1.0000
4.500 0.8809 0.01023 0.00453 -0.0840 0.6078 1.0000
4.750 0.9035 0.01057 0.00473 -0.0827 0.5585 1.0000
5.000 0.9239 0.01110 0.00500 -0.0812 0.4962 1.0000
5.250 0.9424 0.01184 0.00544 -0.0795 0.4250 1.0000
5.500 0.9609 0.01266 0.00594 -0.0780 0.3604 1.0000
5.750 0.9803 0.01344 0.00647 -0.0767 0.3055 1.0000
6.000 0.9995 0.01427 0.00704 -0.0756 0.2520 1.0000
6.250 1.0196 0.01504 0.00760 -0.0746 0.2026 1.0000
6.500 1.0405 0.01577 0.00821 -0.0736 0.1668 1.0000
6.750 1.0602 0.01665 0.00888 -0.0726 0.1212 1.0000
7.000 1.0785 0.01776 0.00983 -0.0714 0.0752 1.0000
7.250 1.0906 0.01979 0.01151 -0.0691 0.0300 1.0000
7.500 1.1049 0.02152 0.01332 -0.0669 0.0189 1.0000
7.750 1.1209 0.02292 0.01486 -0.0650 0.0163 1.0000
8.000 1.1333 0.02480 0.01685 -0.0627 0.0146 1.0000
8.250 1.1440 0.02774 0.01995 -0.0603 0.0137 1.0000
8.500 1.1616 0.03050 0.02290 -0.0587 0.0133 1.0000
8.750 1.1801 0.03322 0.02589 -0.0574 0.0132 1.0000
9.000 1.1960 0.03653 0.02953 -0.0558 0.0132 1.0000
9.250 1.2069 0.04053 0.03393 -0.0539 0.0134 1.0000
9.750 1.2240 0.04658 0.04064 -0.0496 0.0139 1.0000
10.000 1.2300 0.04876 0.04311 -0.0471 0.0142 1.0000
10.250 1.2274 0.05152 0.04625 -0.0437 0.0148 1.0000
10.500 1.2096 0.05592 0.05116 -0.0391 0.0159 1.0000
10.750 1.1849 0.06059 0.05623 -0.0357 0.0167 1.0000
11.000 1.1621 0.06535 0.06128 -0.0339 0.0172 1.0000
11.250 1.1402 0.07033 0.06650 -0.0337 0.0175 1.0000
11.500 1.1188 0.07578 0.07215 -0.0349 0.0177 1.0000
11.750 1.0969 0.08201 0.07857 -0.0375 0.0178 1.0000
12.000 1.0753 0.08912 0.08584 -0.0417 0.0179 1.0000
12.250 1.0548 0.09727 0.09413 -0.0474 0.0177 1.0000
12.500 1.0332 0.10737 0.10434 -0.0549 0.0176 1.0000
12.750 1.0101 0.12032 0.11737 -0.0638 0.0177 1.0000
13.000 0.9885 0.13469 0.13171 -0.0717 0.0184 1.0000
13.250 0.9775 0.14425 0.14124 -0.0766 0.0193 1.0000
13.500 0.9716 0.15194 0.14889 -0.0805 0.0203 1.0000
13.750 0.9673 0.15838 0.15530 -0.0834 0.0216 1.0000
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