HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 100,000 Max Cl/Cd: 39.73 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq010-il-100000.txt Download as CSV file: xf-hq010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6401 0.10723 0.10239 0.0075 1.0000 0.1576
-10.000 -0.6718 0.10162 0.09693 0.0004 1.0000 0.1608
-9.250 -0.8257 0.06229 0.05678 -0.0213 1.0000 0.0670
-9.000 -0.8317 0.05797 0.05208 -0.0201 1.0000 0.0673
-8.750 -0.8345 0.05300 0.04672 -0.0188 1.0000 0.0678
-8.500 -0.8262 0.04814 0.04151 -0.0176 1.0000 0.0670
-8.250 -0.8177 0.04353 0.03648 -0.0162 1.0000 0.0666
-8.000 -0.8086 0.03959 0.03195 -0.0146 1.0000 0.0684
-7.750 -0.7899 0.03659 0.02896 -0.0142 1.0000 0.0720
-7.500 -0.7721 0.03346 0.02536 -0.0128 1.0000 0.0726
-7.250 -0.7514 0.03086 0.02237 -0.0117 1.0000 0.0741
-7.000 -0.7287 0.02862 0.01978 -0.0106 1.0000 0.0765
-6.750 -0.7056 0.02714 0.01785 -0.0095 1.0000 0.0805
-6.500 -0.6818 0.02490 0.01574 -0.0091 1.0000 0.0872
-6.250 -0.6569 0.02338 0.01401 -0.0082 1.0000 0.0930
-6.000 -0.6336 0.02155 0.01233 -0.0074 1.0000 0.1011
-5.750 -0.6124 0.02009 0.01092 -0.0062 1.0000 0.1140
-5.500 -0.5932 0.01875 0.00974 -0.0048 1.0000 0.1360
-5.250 -0.5760 0.01742 0.00875 -0.0031 1.0000 0.1746
-5.000 -0.5639 0.01572 0.00777 -0.0008 1.0000 0.2686
-4.750 -0.5537 0.01430 0.00720 0.0019 1.0000 0.4004
-4.500 -0.5407 0.01361 0.00708 0.0049 1.0000 0.5109
-4.250 -0.5255 0.01347 0.00719 0.0079 1.0000 0.5919
-4.000 -0.5100 0.01354 0.00729 0.0109 1.0000 0.6469
-3.750 -0.4950 0.01368 0.00745 0.0141 1.0000 0.6871
-3.500 -0.4805 0.01383 0.00760 0.0173 1.0000 0.7194
-3.250 -0.4669 0.01400 0.00776 0.0207 1.0000 0.7482
-3.000 -0.4548 0.01422 0.00798 0.0246 1.0000 0.7770
-2.750 -0.4438 0.01443 0.00819 0.0287 1.0000 0.8049
-2.500 -0.4320 0.01454 0.00824 0.0323 1.0000 0.8299
-2.250 -0.4172 0.01460 0.00825 0.0351 1.0000 0.8498
-2.000 -0.4021 0.01458 0.00816 0.0374 1.0000 0.8699
-1.750 -0.3816 0.01464 0.00817 0.0389 1.0000 0.8879
-1.500 -0.3562 0.01475 0.00820 0.0392 1.0000 0.9060
-1.250 -0.3251 0.01489 0.00825 0.0382 1.0000 0.9244
-1.000 -0.2740 0.01526 0.00852 0.0335 0.9971 0.9404
-0.750 -0.2040 0.01579 0.00893 0.0253 0.9941 0.9545
-0.500 -0.1299 0.01612 0.00919 0.0161 0.9917 0.9651
-0.250 -0.0632 0.01624 0.00926 0.0078 0.9868 0.9733
0.000 0.0001 0.01634 0.00935 0.0000 0.9814 0.9814
0.250 0.0633 0.01624 0.00926 -0.0078 0.9733 0.9868
0.500 0.1301 0.01611 0.00918 -0.0161 0.9649 0.9916
0.750 0.2041 0.01578 0.00893 -0.0254 0.9545 0.9941
1.000 0.2740 0.01526 0.00852 -0.0335 0.9405 0.9972
1.250 0.3252 0.01489 0.00825 -0.0382 0.9244 1.0000
1.500 0.3561 0.01475 0.00820 -0.0392 0.9061 1.0000
1.750 0.3816 0.01464 0.00817 -0.0389 0.8880 1.0000
2.000 0.4021 0.01458 0.00816 -0.0374 0.8700 1.0000
2.250 0.4172 0.01460 0.00825 -0.0351 0.8499 1.0000
2.500 0.4320 0.01454 0.00823 -0.0322 0.8299 1.0000
2.750 0.4437 0.01443 0.00819 -0.0287 0.8049 1.0000
3.000 0.4548 0.01422 0.00798 -0.0246 0.7770 1.0000
3.250 0.4668 0.01400 0.00776 -0.0207 0.7482 1.0000
3.500 0.4805 0.01383 0.00760 -0.0173 0.7195 1.0000
3.750 0.4949 0.01368 0.00745 -0.0141 0.6870 1.0000
4.000 0.5100 0.01354 0.00729 -0.0109 0.6468 1.0000
4.250 0.5255 0.01347 0.00719 -0.0079 0.5921 1.0000
4.500 0.5407 0.01361 0.00708 -0.0049 0.5110 1.0000
4.750 0.5538 0.01430 0.00720 -0.0019 0.4005 1.0000
5.000 0.5639 0.01571 0.00776 0.0008 0.2691 1.0000
5.250 0.5760 0.01742 0.00875 0.0031 0.1745 1.0000
5.500 0.5933 0.01875 0.00974 0.0048 0.1360 1.0000
5.750 0.6124 0.02010 0.01092 0.0062 0.1139 1.0000
6.000 0.6336 0.02155 0.01234 0.0074 0.1009 1.0000
6.250 0.6569 0.02338 0.01401 0.0082 0.0930 1.0000
6.500 0.6818 0.02489 0.01574 0.0091 0.0870 1.0000
6.750 0.7056 0.02714 0.01785 0.0095 0.0805 1.0000
7.000 0.7287 0.02862 0.01978 0.0106 0.0764 1.0000
7.250 0.7513 0.03086 0.02238 0.0117 0.0740 1.0000
7.500 0.7721 0.03347 0.02537 0.0128 0.0725 1.0000
7.750 0.7899 0.03660 0.02897 0.0142 0.0720 1.0000
8.000 0.8087 0.03952 0.03191 0.0147 0.0686 1.0000
8.250 0.8177 0.04353 0.03648 0.0162 0.0666 1.0000
8.500 0.8263 0.04813 0.04149 0.0176 0.0670 1.0000
8.750 0.8347 0.05290 0.04662 0.0188 0.0679 1.0000
9.000 0.8327 0.05835 0.05243 0.0199 0.0674 1.0000
9.250 0.8242 0.06200 0.05653 0.0215 0.0669 1.0000
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Polar data table (+)
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