HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 200,000 Max Cl/Cd: 75.84 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3011-il-200000-n5.txt Download as CSV file: xf-hq3011-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3839 0.08751 0.08404 -0.0452 1.0000 0.0140
-9.250 -0.3887 0.08385 0.08044 -0.0460 1.0000 0.0137
-9.000 -0.3995 0.07946 0.07614 -0.0470 1.0000 0.0138
-8.750 -0.4124 0.07629 0.07307 -0.0466 1.0000 0.0136
-8.500 -0.4172 0.07014 0.06697 -0.0522 0.9937 0.0135
-8.250 -0.4161 0.05834 0.05509 -0.0694 0.9787 0.0132
-8.000 -0.4134 0.04795 0.04435 -0.0802 0.9679 0.0129
-7.750 -0.4077 0.03826 0.03405 -0.0863 0.9586 0.0127
-7.500 -0.3977 0.03147 0.02653 -0.0882 0.9490 0.0128
-7.250 -0.3753 0.02687 0.02122 -0.0899 0.9439 0.0131
-7.000 -0.3542 0.02404 0.01787 -0.0898 0.9365 0.0136
-6.750 -0.3271 0.02187 0.01527 -0.0903 0.9316 0.0142
-6.500 -0.3005 0.02033 0.01346 -0.0906 0.9265 0.0152
-6.250 -0.2739 0.01953 0.01257 -0.0909 0.9206 0.0165
-6.000 -0.2448 0.01849 0.01138 -0.0914 0.9164 0.0176
-5.750 -0.2193 0.01746 0.01019 -0.0911 0.9103 0.0187
-5.500 -0.1924 0.01653 0.00908 -0.0910 0.9048 0.0200
-5.250 -0.1651 0.01565 0.00811 -0.0910 0.9001 0.0222
-5.000 -0.1397 0.01510 0.00751 -0.0907 0.8934 0.0258
-4.750 -0.1122 0.01451 0.00686 -0.0907 0.8884 0.0321
-4.500 -0.0859 0.01420 0.00649 -0.0905 0.8822 0.0408
-4.250 -0.0588 0.01390 0.00614 -0.0904 0.8764 0.0496
-4.000 -0.0313 0.01359 0.00582 -0.0904 0.8713 0.0605
-3.750 -0.0054 0.01325 0.00543 -0.0901 0.8647 0.0678
-3.500 0.0223 0.01292 0.00504 -0.0901 0.8596 0.0778
-3.250 0.0484 0.01259 0.00471 -0.0899 0.8532 0.0912
-3.000 0.0753 0.01224 0.00440 -0.0898 0.8474 0.1154
-2.750 0.1018 0.01178 0.00413 -0.0897 0.8418 0.1741
-2.500 0.1268 0.01116 0.00390 -0.0896 0.8351 0.2918
-2.250 0.1513 0.01046 0.00385 -0.0893 0.8299 0.4875
-2.000 0.1765 0.01035 0.00389 -0.0887 0.8224 0.5577
-1.750 0.2039 0.01028 0.00382 -0.0883 0.8166 0.5943
-1.500 0.2301 0.01024 0.00379 -0.0878 0.8089 0.6213
-1.250 0.2565 0.01017 0.00375 -0.0872 0.8024 0.6583
-1.000 0.2818 0.01010 0.00376 -0.0864 0.7945 0.6897
-0.750 0.3088 0.01004 0.00368 -0.0860 0.7880 0.7078
-0.500 0.3353 0.01000 0.00365 -0.0856 0.7803 0.7207
-0.250 0.3630 0.00997 0.00357 -0.0853 0.7739 0.7314
0.000 0.3896 0.00995 0.00357 -0.0850 0.7662 0.7426
0.250 0.4167 0.00991 0.00351 -0.0846 0.7585 0.7550
0.500 0.4425 0.00989 0.00349 -0.0840 0.7472 0.7692
0.750 0.4682 0.00986 0.00347 -0.0833 0.7353 0.7856
1.000 0.4940 0.00986 0.00347 -0.0826 0.7249 0.8041
1.250 0.5200 0.00986 0.00346 -0.0820 0.7161 0.8250
1.500 0.5455 0.00987 0.00350 -0.0814 0.7057 0.8474
1.750 0.5711 0.00987 0.00351 -0.0807 0.6955 0.8689
2.000 0.5971 0.00986 0.00351 -0.0802 0.6846 0.8912
2.250 0.6258 0.00983 0.00349 -0.0801 0.6719 0.9173
2.500 0.6622 0.00982 0.00349 -0.0818 0.6560 0.9644
2.750 0.6913 0.00992 0.00354 -0.0822 0.6394 1.0000
3.000 0.7175 0.01005 0.00362 -0.0819 0.6226 1.0000
3.250 0.7434 0.01019 0.00370 -0.0815 0.6044 1.0000
3.500 0.7690 0.01036 0.00380 -0.0811 0.5842 1.0000
3.750 0.7939 0.01056 0.00394 -0.0806 0.5612 1.0000
4.000 0.8183 0.01080 0.00408 -0.0799 0.5346 1.0000
4.250 0.8418 0.01110 0.00425 -0.0792 0.5052 1.0000
4.500 0.8645 0.01145 0.00447 -0.0783 0.4744 1.0000
4.750 0.8868 0.01184 0.00475 -0.0773 0.4433 1.0000
5.000 0.9087 0.01226 0.00504 -0.0764 0.4133 1.0000
5.250 0.9304 0.01271 0.00538 -0.0754 0.3839 1.0000
5.500 0.9518 0.01318 0.00574 -0.0745 0.3558 1.0000
5.750 0.9729 0.01366 0.00614 -0.0735 0.3289 1.0000
6.000 0.9940 0.01416 0.00655 -0.0725 0.3051 1.0000
6.250 1.0148 0.01466 0.00699 -0.0715 0.2837 1.0000
6.500 1.0356 0.01518 0.00745 -0.0705 0.2635 1.0000
6.750 1.0558 0.01571 0.00793 -0.0695 0.2441 1.0000
7.000 1.0763 0.01623 0.00843 -0.0684 0.2243 1.0000
7.250 1.0959 0.01678 0.00893 -0.0673 0.2054 1.0000
7.500 1.1150 0.01736 0.00947 -0.0661 0.1870 1.0000
7.750 1.1334 0.01797 0.01002 -0.0649 0.1670 1.0000
8.000 1.1503 0.01867 0.01063 -0.0635 0.1471 1.0000
8.250 1.1680 0.01931 0.01127 -0.0621 0.1298 1.0000
8.500 1.1837 0.02001 0.01191 -0.0605 0.1117 1.0000
9.000 1.2113 0.02157 0.01336 -0.0568 0.0803 1.0000
9.250 1.2243 0.02243 0.01418 -0.0549 0.0667 1.0000
9.500 1.2364 0.02336 0.01507 -0.0530 0.0545 1.0000
9.750 1.2490 0.02426 0.01599 -0.0512 0.0471 1.0000
10.000 1.2623 0.02513 0.01693 -0.0495 0.0417 1.0000
10.250 1.2737 0.02614 0.01801 -0.0477 0.0364 1.0000
10.500 1.2849 0.02719 0.01913 -0.0460 0.0299 1.0000
10.750 1.2932 0.02850 0.02043 -0.0441 0.0215 1.0000
11.000 1.3004 0.02993 0.02187 -0.0423 0.0150 1.0000
11.250 1.3065 0.03149 0.02347 -0.0405 0.0105 1.0000
11.500 1.3125 0.03308 0.02514 -0.0388 0.0087 1.0000
11.750 1.3189 0.03469 0.02687 -0.0372 0.0078 1.0000
12.000 1.3236 0.03650 0.02881 -0.0358 0.0070 1.0000
12.250 1.3274 0.03844 0.03088 -0.0344 0.0066 1.0000
12.500 1.3301 0.04056 0.03314 -0.0332 0.0063 1.0000
12.750 1.3313 0.04289 0.03562 -0.0321 0.0061 1.0000
13.000 1.3307 0.04551 0.03843 -0.0313 0.0059 1.0000
13.250 1.3302 0.04821 0.04131 -0.0306 0.0058 1.0000
13.500 1.3278 0.05123 0.04451 -0.0302 0.0056 1.0000
13.750 1.3237 0.05459 0.04805 -0.0301 0.0055 1.0000
14.000 1.3188 0.05820 0.05184 -0.0304 0.0055 1.0000
14.250 1.3124 0.06221 0.05603 -0.0310 0.0054 1.0000
14.500 1.3054 0.06652 0.06052 -0.0319 0.0054 1.0000
14.750 1.2969 0.07130 0.06548 -0.0333 0.0053 1.0000
15.000 1.2869 0.07658 0.07094 -0.0352 0.0053 1.0000
15.250 1.2761 0.08227 0.07681 -0.0375 0.0052 1.0000
15.500 1.2650 0.08828 0.08300 -0.0402 0.0052 1.0000
15.750 1.2525 0.09481 0.08971 -0.0433 0.0052 1.0000
16.000 1.2404 0.10148 0.09655 -0.0466 0.0052 1.0000
16.250 1.2267 0.10870 0.10394 -0.0503 0.0052 1.0000
16.500 1.2136 0.11599 0.11139 -0.0542 0.0052 1.0000
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