HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 500,000 Max Cl/Cd: 99.5 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq308-il-500000-n5.txt Download as CSV file: xf-hq308-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3629 0.08886 0.08666 -0.0328 1.0000 0.0053
-8.000 -0.3632 0.08604 0.08387 -0.0331 1.0000 0.0053
-7.750 -0.3664 0.08354 0.08142 -0.0326 1.0000 0.0053
-7.500 -0.3579 0.07927 0.07717 -0.0365 0.9947 0.0053
-7.250 -0.3427 0.07426 0.07218 -0.0429 0.9872 0.0053
-7.000 -0.3275 0.06820 0.06612 -0.0514 0.9800 0.0049
-6.750 -0.3014 0.06084 0.05868 -0.0643 0.9744 0.0045
-6.500 -0.2768 0.05434 0.05209 -0.0740 0.9658 0.0043
-6.250 -0.2502 0.04790 0.04549 -0.0822 0.9582 0.0041
-6.000 -0.2255 0.04212 0.03951 -0.0876 0.9491 0.0038
-5.750 -0.2022 0.03666 0.03378 -0.0909 0.9397 0.0037
-5.500 -0.1779 0.03150 0.02829 -0.0930 0.9314 0.0036
-5.250 -0.1536 0.02639 0.02277 -0.0939 0.9231 0.0035
-5.000 -0.1286 0.02124 0.01712 -0.0940 0.9156 0.0036
-4.750 -0.1026 0.01725 0.01258 -0.0937 0.9089 0.0041
-4.500 -0.0761 0.01508 0.01001 -0.0934 0.9023 0.0045
-4.250 -0.0491 0.01396 0.00863 -0.0932 0.8960 0.0050
-4.000 -0.0228 0.01253 0.00693 -0.0930 0.8897 0.0063
-3.750 0.0039 0.01168 0.00595 -0.0928 0.8832 0.0069
-3.500 0.0308 0.01075 0.00485 -0.0924 0.8770 0.0071
-3.250 0.0577 0.01004 0.00399 -0.0922 0.8703 0.0077
-3.000 0.0850 0.00949 0.00332 -0.0920 0.8641 0.0086
-2.750 0.1125 0.00909 0.00283 -0.0918 0.8573 0.0097
-2.500 0.1400 0.00880 0.00243 -0.0917 0.8509 0.0113
-2.250 0.1677 0.00853 0.00204 -0.0916 0.8436 0.0121
-2.000 0.1954 0.00836 0.00178 -0.0914 0.8362 0.0144
-1.750 0.2228 0.00817 0.00158 -0.0913 0.8269 0.0300
-1.500 0.2502 0.00798 0.00145 -0.0912 0.8166 0.0612
-1.250 0.2776 0.00783 0.00133 -0.0911 0.8073 0.0918
-0.750 0.3296 0.00639 0.00123 -0.0914 0.7889 0.5673
-0.500 0.3556 0.00624 0.00126 -0.0909 0.7761 0.6502
-0.250 0.3813 0.00616 0.00130 -0.0903 0.7621 0.7106
0.000 0.4078 0.00615 0.00130 -0.0899 0.7501 0.7422
0.250 0.4350 0.00617 0.00129 -0.0897 0.7388 0.7534
0.500 0.4621 0.00620 0.00129 -0.0895 0.7266 0.7647
0.750 0.4887 0.00624 0.00129 -0.0892 0.7102 0.7769
1.000 0.5149 0.00631 0.00130 -0.0887 0.6892 0.7901
1.250 0.5410 0.00638 0.00132 -0.0883 0.6684 0.8046
1.500 0.5669 0.00644 0.00137 -0.0878 0.6505 0.8216
1.750 0.5925 0.00649 0.00142 -0.0873 0.6312 0.8423
2.000 0.6167 0.00652 0.00147 -0.0864 0.6089 0.8733
2.250 0.6479 0.00653 0.00150 -0.0871 0.5794 1.0000
2.500 0.6736 0.00677 0.00162 -0.0868 0.5464 1.0000
2.750 0.6987 0.00707 0.00175 -0.0863 0.5074 1.0000
3.000 0.7236 0.00741 0.00191 -0.0859 0.4665 1.0000
3.250 0.7483 0.00778 0.00210 -0.0854 0.4260 1.0000
3.500 0.7731 0.00814 0.00231 -0.0850 0.3891 1.0000
3.750 0.7973 0.00858 0.00258 -0.0845 0.3433 1.0000
4.000 0.8208 0.00910 0.00285 -0.0840 0.2918 1.0000
4.250 0.8440 0.00967 0.00316 -0.0834 0.2383 1.0000
4.500 0.8650 0.01050 0.00356 -0.0826 0.1621 1.0000
4.750 0.8884 0.01105 0.00390 -0.0821 0.1218 1.0000
5.000 0.9119 0.01158 0.00426 -0.0815 0.0879 1.0000
5.250 0.9354 0.01211 0.00469 -0.0810 0.0600 1.0000
5.500 0.9590 0.01263 0.00512 -0.0804 0.0389 1.0000
5.750 0.9808 0.01338 0.00570 -0.0796 0.0119 1.0000
6.000 1.0042 0.01393 0.00623 -0.0789 0.0042 1.0000
6.250 1.0284 0.01437 0.00674 -0.0784 0.0036 1.0000
6.500 1.0520 0.01488 0.00735 -0.0777 0.0032 1.0000
6.750 1.0752 0.01543 0.00799 -0.0770 0.0030 1.0000
7.000 1.0978 0.01604 0.00876 -0.0762 0.0028 1.0000
7.250 1.1198 0.01673 0.00956 -0.0752 0.0027 1.0000
7.500 1.1409 0.01751 0.01046 -0.0742 0.0027 1.0000
7.750 1.1609 0.01839 0.01147 -0.0730 0.0026 1.0000
8.000 1.1801 0.01934 0.01254 -0.0717 0.0026 1.0000
8.250 1.1977 0.02044 0.01377 -0.0702 0.0025 1.0000
8.500 1.2133 0.02173 0.01520 -0.0686 0.0023 1.0000
8.750 1.2232 0.02374 0.01740 -0.0661 0.0020 1.0000
9.000 1.2366 0.02533 0.01916 -0.0641 0.0018 1.0000
9.250 1.2535 0.02630 0.02027 -0.0627 0.0017 1.0000
9.500 1.2663 0.02778 0.02193 -0.0608 0.0017 1.0000
9.750 1.2775 0.02926 0.02364 -0.0587 0.0016 1.0000
10.000 1.2850 0.03088 0.02546 -0.0560 0.0015 1.0000
10.250 1.2898 0.03265 0.02744 -0.0531 0.0015 1.0000
10.500 1.2931 0.03449 0.02949 -0.0503 0.0014 1.0000
10.750 1.2933 0.03665 0.03187 -0.0475 0.0013 1.0000
11.000 1.2905 0.03913 0.03458 -0.0448 0.0013 1.0000
11.250 1.2865 0.04175 0.03743 -0.0425 0.0013 1.0000
11.500 1.2794 0.04483 0.04074 -0.0405 0.0012 1.0000
11.750 1.2709 0.04819 0.04433 -0.0391 0.0012 1.0000
12.000 1.2600 0.05209 0.04845 -0.0384 0.0012 1.0000
12.250 1.2479 0.05644 0.05301 -0.0384 0.0011 1.0000
12.500 1.2329 0.06163 0.05841 -0.0394 0.0011 1.0000
12.750 1.2160 0.06768 0.06467 -0.0416 0.0011 1.0000
13.000 1.1999 0.07425 0.07142 -0.0447 0.0011 1.0000
13.250 1.1830 0.08176 0.07911 -0.0490 0.0011 1.0000
13.500 1.1641 0.09067 0.08820 -0.0545 0.0012 1.0000
13.750 1.1454 0.10046 0.09815 -0.0607 0.0012 1.0000
14.000 1.1259 0.11120 0.10902 -0.0673 0.0012 1.0000
14.250 1.1076 0.12202 0.11995 -0.0737 0.0013 1.0000
14.500 1.0889 0.13332 0.13134 -0.0800 0.0013 1.0000
14.750 1.0689 0.14538 0.14347 -0.0864 0.0014 1.0000
15.000 1.0488 0.15814 0.15627 -0.0929 0.0015 1.0000
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Polar data table (+)
Polar graphs
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