HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 50,000 Max Cl/Cd: 37.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq208-il-50000.txt Download as CSV file: xf-hq208-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4458 0.09402 0.08753 -0.0107 1.0000 0.2645
-7.500 -0.4434 0.09127 0.08485 -0.0100 1.0000 0.2824
-7.250 -0.4546 0.08956 0.08329 -0.0095 1.0000 0.2994
-7.000 -0.4421 0.08615 0.07985 -0.0072 1.0000 0.3257
-6.750 -0.4244 0.08250 0.07622 -0.0041 1.0000 0.3612
-6.500 -0.4204 0.08005 0.07384 -0.0015 1.0000 0.3924
-6.250 -0.4245 0.07825 0.07216 0.0016 1.0000 0.4222
-6.000 -0.3980 0.07393 0.06783 0.0038 1.0000 0.4569
-4.750 -0.3850 0.04303 0.03517 -0.0440 1.0000 0.1351
-4.500 -0.3617 0.03904 0.03061 -0.0441 1.0000 0.1211
-4.250 -0.3387 0.03541 0.02648 -0.0437 1.0000 0.1126
-4.000 -0.3134 0.03263 0.02302 -0.0430 1.0000 0.1075
-3.750 -0.2890 0.03000 0.01997 -0.0421 1.0000 0.1066
-3.500 -0.2635 0.02789 0.01731 -0.0409 1.0000 0.1089
-3.250 -0.2404 0.02598 0.01529 -0.0400 1.0000 0.1218
-3.000 -0.2164 0.02409 0.01333 -0.0385 1.0000 0.1344
-2.750 -0.1931 0.02242 0.01168 -0.0370 1.0000 0.1635
-2.500 -0.1690 0.02032 0.00999 -0.0359 1.0000 0.2308
-2.250 -0.1392 0.01665 0.00940 -0.0274 1.0000 1.0000
-2.000 -0.1282 0.01648 0.00877 -0.0259 1.0000 1.0000
-1.750 -0.1099 0.01644 0.00827 -0.0255 1.0000 1.0000
-1.500 -0.0889 0.01649 0.00789 -0.0254 1.0000 1.0000
-1.250 -0.0671 0.01659 0.00763 -0.0253 1.0000 1.0000
-1.000 -0.0449 0.01675 0.00746 -0.0253 1.0000 1.0000
-0.750 -0.0228 0.01694 0.00732 -0.0252 1.0000 1.0000
-0.500 -0.0009 0.01718 0.00731 -0.0251 1.0000 1.0000
-0.250 0.0209 0.01745 0.00736 -0.0249 1.0000 1.0000
0.000 0.0424 0.01776 0.00748 -0.0248 1.0000 1.0000
0.250 0.0637 0.01810 0.00767 -0.0246 1.0000 1.0000
0.500 0.0847 0.01848 0.00788 -0.0245 1.0000 1.0000
0.750 0.1055 0.01890 0.00818 -0.0243 1.0000 1.0000
1.000 0.1260 0.01936 0.00855 -0.0242 1.0000 1.0000
1.250 0.1461 0.01986 0.00898 -0.0241 1.0000 1.0000
1.500 0.1660 0.02041 0.00948 -0.0240 1.0000 1.0000
1.750 0.1854 0.02101 0.01004 -0.0239 1.0000 1.0000
2.000 0.2046 0.02165 0.01067 -0.0239 1.0000 1.0000
2.250 0.2232 0.02236 0.01137 -0.0240 1.0000 1.0000
2.500 0.2414 0.02314 0.01216 -0.0240 1.0000 1.0000
2.750 0.2879 0.02446 0.01358 -0.0296 0.9852 1.0000
3.000 0.3555 0.02588 0.01520 -0.0383 0.9577 1.0000
3.250 0.4133 0.02689 0.01641 -0.0448 0.9317 1.0000
3.500 0.4694 0.02763 0.01740 -0.0503 0.9049 1.0000
3.750 0.5266 0.02807 0.01822 -0.0553 0.8767 1.0000
4.000 0.5915 0.02799 0.01855 -0.0605 0.8470 1.0000
4.250 0.6447 0.02759 0.01856 -0.0630 0.8130 1.0000
4.500 0.7040 0.02631 0.01784 -0.0645 0.7777 1.0000
4.750 0.7461 0.02503 0.01692 -0.0627 0.7346 1.0000
5.000 0.7847 0.02338 0.01551 -0.0593 0.6840 1.0000
5.250 0.8100 0.02232 0.01446 -0.0546 0.6188 1.0000
5.500 0.8296 0.02194 0.01395 -0.0500 0.5421 1.0000
5.750 0.8456 0.02243 0.01402 -0.0460 0.4583 1.0000
6.000 0.8578 0.02381 0.01479 -0.0424 0.3632 1.0000
6.250 0.8708 0.02641 0.01650 -0.0393 0.2639 1.0000
6.500 0.8919 0.02899 0.01873 -0.0377 0.2054 1.0000
6.750 0.9149 0.03112 0.02080 -0.0365 0.1726 1.0000
7.000 0.9430 0.03396 0.02366 -0.0358 0.1538 1.0000
7.250 0.9640 0.03638 0.02636 -0.0344 0.1341 1.0000
7.500 0.9860 0.03995 0.03032 -0.0330 0.1216 1.0000
7.750 1.0030 0.04385 0.03475 -0.0313 0.1102 1.0000
8.000 1.0155 0.04745 0.03868 -0.0296 0.0982 1.0000
8.250 1.0278 0.05122 0.04260 -0.0282 0.0883 1.0000
8.500 1.0308 0.05575 0.04783 -0.0260 0.0860 1.0000
8.750 1.0311 0.06080 0.05340 -0.0242 0.0861 1.0000
9.000 1.0273 0.06597 0.05897 -0.0228 0.0869 1.0000
9.250 1.0214 0.07117 0.06447 -0.0216 0.0880 1.0000
9.500 1.0184 0.07658 0.07004 -0.0210 0.0892 1.0000
9.750 0.9835 0.08118 0.07504 -0.0204 0.0925 1.0000
10.000 0.9446 0.08710 0.08109 -0.0224 0.0962 1.0000
10.250 0.9237 0.09383 0.08784 -0.0258 0.0993 1.0000
10.500 0.9171 0.10016 0.09416 -0.0282 0.1016 1.0000
10.750 0.8600 0.12034 0.11407 -0.0480 0.1514 1.0000
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Polar data table (+)
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