HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.89 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq308-il-1000000-n5.txt Download as CSV file: xf-hq308-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3025 0.11543 0.11385 -0.0274 1.0000 0.0038
-7.250 -0.3175 0.06627 0.06473 -0.0567 0.9741 0.0023
-7.000 -0.2911 0.05907 0.05749 -0.0701 0.9629 0.0023
-6.500 -0.2535 0.04613 0.04427 -0.0858 0.9311 0.0021
-6.250 -0.2382 0.04075 0.03867 -0.0889 0.9173 0.0021
-6.000 -0.2209 0.03547 0.03314 -0.0910 0.9061 0.0020
-5.750 -0.2018 0.02944 0.02675 -0.0923 0.8960 0.0020
-5.500 -0.1861 0.01467 0.01064 -0.0921 0.8860 0.0020
-5.250 -0.1604 0.01281 0.00841 -0.0918 0.8795 0.0023
-5.000 -0.1336 0.01205 0.00745 -0.0917 0.8730 0.0024
-4.500 -0.0807 0.01030 0.00538 -0.0914 0.8603 0.0030
-4.250 -0.0536 0.00991 0.00490 -0.0914 0.8539 0.0032
-4.000 -0.0264 0.00943 0.00434 -0.0913 0.8477 0.0035
-3.750 0.0008 0.00902 0.00383 -0.0912 0.8413 0.0040
-3.500 0.0284 0.00879 0.00355 -0.0911 0.8351 0.0047
-3.250 0.0558 0.00848 0.00315 -0.0910 0.8281 0.0051
-3.000 0.0834 0.00814 0.00273 -0.0910 0.8213 0.0053
-2.750 0.1107 0.00748 0.00188 -0.0908 0.8128 0.0071
-2.500 0.1383 0.00728 0.00161 -0.0907 0.8020 0.0078
-2.250 0.1658 0.00715 0.00140 -0.0906 0.7906 0.0088
-2.000 0.1936 0.00703 0.00121 -0.0905 0.7810 0.0090
-1.750 0.2214 0.00695 0.00104 -0.0904 0.7724 0.0093
-1.500 0.2491 0.00689 0.00093 -0.0904 0.7618 0.0101
-1.250 0.2765 0.00679 0.00082 -0.0903 0.7475 0.0304
-1.000 0.3037 0.00674 0.00076 -0.0902 0.7318 0.0476
-0.750 0.3312 0.00666 0.00071 -0.0901 0.7187 0.0787
-0.500 0.3587 0.00651 0.00067 -0.0902 0.7067 0.1371
-0.250 0.3847 0.00558 0.00064 -0.0906 0.6944 0.4807
0.000 0.4109 0.00533 0.00071 -0.0904 0.6779 0.6168
0.250 0.4371 0.00530 0.00077 -0.0900 0.6559 0.6795
0.500 0.4636 0.00538 0.00081 -0.0898 0.6322 0.7039
0.750 0.4906 0.00548 0.00084 -0.0896 0.6107 0.7139
1.000 0.5176 0.00558 0.00088 -0.0894 0.5898 0.7236
1.250 0.5443 0.00571 0.00094 -0.0892 0.5658 0.7334
1.500 0.5707 0.00588 0.00101 -0.0890 0.5348 0.7440
1.750 0.5967 0.00608 0.00110 -0.0887 0.5013 0.7553
2.000 0.6224 0.00632 0.00121 -0.0884 0.4631 0.7671
2.250 0.6480 0.00655 0.00134 -0.0880 0.4269 0.7801
2.500 0.6737 0.00677 0.00148 -0.0877 0.3945 0.7943
2.750 0.6992 0.00700 0.00162 -0.0874 0.3627 0.8104
3.000 0.7236 0.00730 0.00180 -0.0868 0.3172 0.8307
3.250 0.7466 0.00765 0.00200 -0.0860 0.2653 0.8606
3.500 0.7734 0.00775 0.00216 -0.0859 0.2295 1.0000
3.750 0.7974 0.00827 0.00243 -0.0855 0.1762 1.0000
4.000 0.8211 0.00881 0.00271 -0.0850 0.1264 1.0000
4.250 0.8449 0.00935 0.00302 -0.0845 0.0819 1.0000
4.500 0.8686 0.00990 0.00336 -0.0839 0.0445 1.0000
4.750 0.8930 0.01036 0.00370 -0.0835 0.0209 1.0000
5.000 0.9184 0.01067 0.00397 -0.0831 0.0134 1.0000
5.250 0.9431 0.01108 0.00438 -0.0827 0.0038 1.0000
5.500 0.9685 0.01139 0.00471 -0.0823 0.0031 1.0000
5.750 0.9936 0.01175 0.00511 -0.0819 0.0023 1.0000
6.000 1.0183 0.01217 0.00563 -0.0814 0.0019 1.0000
6.250 1.0428 0.01258 0.00610 -0.0809 0.0018 1.0000
6.500 1.0668 0.01305 0.00663 -0.0803 0.0018 1.0000
6.750 1.0902 0.01359 0.00724 -0.0796 0.0018 1.0000
7.000 1.1133 0.01418 0.00793 -0.0788 0.0017 1.0000
7.250 1.1361 0.01476 0.00859 -0.0781 0.0016 1.0000
7.500 1.1587 0.01534 0.00923 -0.0773 0.0015 1.0000
7.750 1.1808 0.01596 0.00991 -0.0765 0.0013 1.0000
8.000 1.2023 0.01664 0.01067 -0.0756 0.0012 1.0000
8.250 1.2225 0.01746 0.01159 -0.0745 0.0011 1.0000
8.500 1.2421 0.01832 0.01255 -0.0733 0.0011 1.0000
8.750 1.2609 0.01923 0.01357 -0.0721 0.0010 1.0000
9.000 1.2790 0.02019 0.01463 -0.0707 0.0010 1.0000
9.250 1.2973 0.02108 0.01561 -0.0695 0.0009 1.0000
9.500 1.3136 0.02214 0.01682 -0.0679 0.0009 1.0000
9.750 1.3292 0.02320 0.01798 -0.0664 0.0008 1.0000
10.000 1.3419 0.02451 0.01942 -0.0644 0.0007 1.0000
10.250 1.3497 0.02624 0.02132 -0.0619 0.0007 1.0000
10.500 1.3427 0.02902 0.02437 -0.0571 0.0006 1.0000
10.750 1.3479 0.03038 0.02587 -0.0543 0.0006 1.0000
11.000 1.3501 0.03202 0.02767 -0.0513 0.0006 1.0000
11.250 1.3556 0.03334 0.02913 -0.0490 0.0006 1.0000
11.500 1.3566 0.03517 0.03112 -0.0466 0.0006 1.0000
11.750 1.3589 0.03694 0.03303 -0.0445 0.0005 1.0000
12.000 1.3556 0.03938 0.03564 -0.0425 0.0005 1.0000
12.250 1.3528 0.04189 0.03832 -0.0409 0.0005 1.0000
12.500 1.3439 0.04526 0.04188 -0.0396 0.0005 1.0000
12.750 1.3325 0.04922 0.04603 -0.0390 0.0005 1.0000
13.000 1.3222 0.05335 0.05034 -0.0391 0.0005 1.0000
13.250 1.3103 0.05810 0.05526 -0.0400 0.0005 1.0000
13.500 1.2943 0.06398 0.06132 -0.0420 0.0005 1.0000
13.750 1.2770 0.07077 0.06828 -0.0451 0.0005 1.0000
14.000 1.2571 0.07888 0.07657 -0.0496 0.0004 1.0000
14.250 1.2395 0.08747 0.08531 -0.0547 0.0004 1.0000
14.500 1.2209 0.09702 0.09501 -0.0606 0.0004 1.0000
14.750 1.1980 0.10821 0.10633 -0.0673 0.0005 1.0000
15.000 1.1753 0.11968 0.11792 -0.0739 0.0005 1.0000
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Polar data table (+)
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