HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.69 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq309-il-1000000.txt Download as CSV file: xf-hq309-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3679 0.08595 0.08440 -0.0360 1.0000 0.0072
-8.250 -0.3732 0.08271 0.08120 -0.0359 1.0000 0.0073
-8.000 -0.3748 0.07915 0.07767 -0.0373 0.9992 0.0073
-7.750 -0.3593 0.07319 0.07171 -0.0451 0.9947 0.0073
-7.500 -0.2754 0.04891 0.04752 -0.0608 0.9823 0.0086
-7.250 -0.2683 0.03990 0.03845 -0.0759 0.9712 0.0086
-7.000 -0.2584 0.03425 0.03267 -0.0822 0.9589 0.0089
-6.750 -0.2514 0.02933 0.02760 -0.0852 0.9452 0.0092
-6.500 -0.2418 0.02509 0.02319 -0.0867 0.9334 0.0097
-6.250 -0.2295 0.02083 0.01871 -0.0877 0.9235 0.0104
-4.750 -0.1030 0.01180 0.00709 -0.0931 0.8972 0.0078
-4.500 -0.0769 0.01082 0.00595 -0.0927 0.8905 0.0076
-4.250 -0.0512 0.00964 0.00459 -0.0922 0.8844 0.0078
-4.000 -0.0251 0.00875 0.00356 -0.0919 0.8777 0.0087
-3.750 0.0020 0.00838 0.00312 -0.0917 0.8718 0.0098
-3.500 0.0293 0.00804 0.00271 -0.0916 0.8651 0.0107
-3.250 0.0567 0.00777 0.00234 -0.0914 0.8589 0.0113
-3.000 0.0843 0.00750 0.00200 -0.0913 0.8512 0.0127
-2.750 0.1118 0.00718 0.00164 -0.0911 0.8436 0.0223
-2.500 0.1394 0.00699 0.00149 -0.0910 0.8356 0.0442
-2.250 0.1671 0.00686 0.00138 -0.0910 0.8288 0.0585
-2.000 0.1948 0.00668 0.00126 -0.0910 0.8215 0.0864
-1.750 0.2216 0.00611 0.00112 -0.0912 0.8148 0.2352
-1.500 0.2472 0.00528 0.00102 -0.0913 0.8069 0.4902
-1.250 0.2745 0.00512 0.00100 -0.0912 0.7974 0.5565
-1.000 0.3018 0.00506 0.00097 -0.0910 0.7870 0.5953
-0.750 0.3293 0.00504 0.00095 -0.0908 0.7770 0.6233
-0.500 0.3570 0.00501 0.00094 -0.0907 0.7676 0.6472
-0.250 0.3845 0.00499 0.00095 -0.0906 0.7587 0.6718
0.000 0.4115 0.00498 0.00099 -0.0903 0.7488 0.7086
0.250 0.4385 0.00499 0.00101 -0.0901 0.7365 0.7356
0.500 0.4658 0.00502 0.00102 -0.0899 0.7237 0.7490
0.750 0.4933 0.00504 0.00104 -0.0898 0.7118 0.7597
1.000 0.5207 0.00508 0.00106 -0.0896 0.6997 0.7700
1.250 0.5479 0.00512 0.00109 -0.0895 0.6865 0.7808
1.500 0.5751 0.00517 0.00112 -0.0893 0.6729 0.7927
1.750 0.6019 0.00523 0.00117 -0.0891 0.6577 0.8056
2.000 0.6284 0.00530 0.00122 -0.0887 0.6406 0.8199
2.250 0.6547 0.00536 0.00129 -0.0884 0.6215 0.8370
2.500 0.6801 0.00542 0.00135 -0.0879 0.5994 0.8593
2.750 0.7030 0.00542 0.00142 -0.0867 0.5737 0.9076
3.000 0.7351 0.00554 0.00150 -0.0877 0.5408 1.0000
3.250 0.7606 0.00582 0.00162 -0.0874 0.5038 1.0000
3.500 0.7859 0.00612 0.00178 -0.0870 0.4666 1.0000
3.750 0.8109 0.00646 0.00196 -0.0866 0.4274 1.0000
4.000 0.8357 0.00681 0.00215 -0.0862 0.3899 1.0000
4.250 0.8602 0.00720 0.00236 -0.0857 0.3477 1.0000
4.500 0.8833 0.00772 0.00263 -0.0851 0.2931 1.0000
4.750 0.9068 0.00821 0.00290 -0.0845 0.2476 1.0000
5.000 0.9308 0.00864 0.00315 -0.0840 0.2123 1.0000
5.250 0.9556 0.00900 0.00340 -0.0836 0.1873 1.0000
5.500 0.9802 0.00935 0.00366 -0.0832 0.1642 1.0000
5.750 1.0038 0.00980 0.00398 -0.0826 0.1354 1.0000
6.000 1.0263 0.01038 0.00434 -0.0819 0.0988 1.0000
6.250 1.0479 0.01103 0.00478 -0.0811 0.0634 1.0000
6.500 1.0692 0.01172 0.00528 -0.0801 0.0343 1.0000
6.750 1.0919 0.01226 0.00573 -0.0794 0.0196 1.0000
7.000 1.1127 0.01300 0.00637 -0.0783 0.0053 1.0000
7.250 1.1357 0.01349 0.00691 -0.0776 0.0043 1.0000
7.500 1.1585 0.01399 0.00749 -0.0767 0.0038 1.0000
7.750 1.1807 0.01456 0.00814 -0.0758 0.0036 1.0000
8.000 1.2015 0.01526 0.00895 -0.0747 0.0034 1.0000
8.250 1.2216 0.01601 0.00980 -0.0735 0.0034 1.0000
8.500 1.2401 0.01688 0.01079 -0.0720 0.0034 1.0000
8.750 1.2581 0.01775 0.01176 -0.0705 0.0034 1.0000
9.000 1.2744 0.01875 0.01287 -0.0688 0.0034 1.0000
9.250 1.2889 0.01985 0.01411 -0.0668 0.0034 1.0000
9.500 1.3009 0.02112 0.01551 -0.0644 0.0033 1.0000
9.750 1.3086 0.02271 0.01725 -0.0615 0.0033 1.0000
10.000 1.3226 0.02344 0.01807 -0.0595 0.0031 1.0000
10.250 1.3299 0.02468 0.01942 -0.0565 0.0031 1.0000
10.500 1.3333 0.02633 0.02122 -0.0532 0.0031 1.0000
10.750 1.3383 0.02787 0.02290 -0.0503 0.0031 1.0000
11.000 1.3433 0.02943 0.02459 -0.0477 0.0031 1.0000
11.250 1.3474 0.03108 0.02638 -0.0452 0.0031 1.0000
11.500 1.3482 0.03314 0.02861 -0.0426 0.0031 1.0000
11.750 1.3462 0.03557 0.03123 -0.0401 0.0031 1.0000
12.000 1.3463 0.03772 0.03353 -0.0381 0.0031 1.0000
12.250 1.3396 0.04080 0.03681 -0.0361 0.0031 1.0000
12.500 1.3330 0.04394 0.04013 -0.0345 0.0031 1.0000
12.750 1.3322 0.04637 0.04269 -0.0337 0.0030 1.0000
13.000 1.3143 0.05132 0.04787 -0.0329 0.0031 1.0000
13.250 1.3052 0.05527 0.05199 -0.0330 0.0031 1.0000
13.500 1.2989 0.05908 0.05596 -0.0336 0.0030 1.0000
13.750 1.2787 0.06535 0.06244 -0.0352 0.0030 1.0000
14.000 1.2710 0.07008 0.06730 -0.0371 0.0030 1.0000
14.250 1.2558 0.07652 0.07390 -0.0401 0.0030 1.0000
14.500 1.2350 0.08467 0.08224 -0.0444 0.0030 1.0000
14.750 1.2146 0.09349 0.09123 -0.0496 0.0030 1.0000
15.000 1.1968 0.10242 0.10030 -0.0550 0.0030 1.0000
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