HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 100,000 Max Cl/Cd: 51.22 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2012-il-100000-n5.txt Download as CSV file: xf-hq2012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4860 0.09462 0.08950 -0.0387 1.0000 0.0274
-10.750 -0.4969 0.08766 0.08260 -0.0423 1.0000 0.0272
-10.500 -0.5170 0.07768 0.07268 -0.0481 1.0000 0.0267
-10.250 -0.5498 0.06652 0.06149 -0.0566 1.0000 0.0259
-10.000 -0.5816 0.05944 0.05433 -0.0613 1.0000 0.0256
-9.750 -0.6096 0.05499 0.04977 -0.0620 1.0000 0.0252
-9.500 -0.6329 0.05150 0.04612 -0.0602 1.0000 0.0252
-9.250 -0.6495 0.04809 0.04249 -0.0580 1.0000 0.0253
-9.000 -0.6608 0.04498 0.03913 -0.0554 1.0000 0.0255
-8.750 -0.6686 0.04214 0.03601 -0.0524 1.0000 0.0258
-8.500 -0.6733 0.03956 0.03312 -0.0492 1.0000 0.0263
-8.250 -0.6745 0.03715 0.03038 -0.0461 1.0000 0.0268
-8.000 -0.6660 0.03447 0.02724 -0.0445 0.9982 0.0278
-7.750 -0.6388 0.03159 0.02379 -0.0461 0.9920 0.0298
-7.500 -0.6097 0.03009 0.02224 -0.0478 0.9860 0.0322
-7.250 -0.5798 0.02844 0.02031 -0.0492 0.9803 0.0353
-7.000 -0.5496 0.02661 0.01810 -0.0501 0.9746 0.0382
-6.750 -0.5180 0.02531 0.01681 -0.0519 0.9699 0.0428
-6.500 -0.4891 0.02424 0.01549 -0.0525 0.9631 0.0483
-6.250 -0.4569 0.02313 0.01436 -0.0541 0.9582 0.0550
-6.000 -0.4264 0.02226 0.01330 -0.0549 0.9524 0.0620
-5.750 -0.3964 0.02134 0.01241 -0.0560 0.9465 0.0702
-5.500 -0.3626 0.02048 0.01149 -0.0576 0.9423 0.0800
-5.250 -0.3361 0.01983 0.01075 -0.0576 0.9348 0.0890
-5.000 -0.3047 0.01911 0.01003 -0.0587 0.9295 0.1027
-4.750 -0.2770 0.01843 0.00943 -0.0591 0.9230 0.1199
-4.500 -0.2481 0.01780 0.00885 -0.0597 0.9168 0.1466
-4.250 -0.2176 0.01708 0.00834 -0.0607 0.9119 0.1960
-4.000 -0.1936 0.01639 0.00793 -0.0605 0.9042 0.2638
-3.750 -0.1667 0.01548 0.00763 -0.0609 0.8991 0.3875
-3.500 -0.1445 0.01517 0.00768 -0.0597 0.8913 0.4967
-3.250 -0.1160 0.01510 0.00772 -0.0594 0.8858 0.5623
-3.000 -0.0900 0.01515 0.00776 -0.0586 0.8790 0.6048
-2.750 -0.0628 0.01521 0.00779 -0.0580 0.8726 0.6372
-2.500 -0.0344 0.01526 0.00777 -0.0577 0.8672 0.6639
-2.250 -0.0096 0.01534 0.00781 -0.0567 0.8596 0.6841
-2.000 0.0200 0.01534 0.00774 -0.0566 0.8547 0.7022
-1.750 0.0435 0.01542 0.00776 -0.0555 0.8465 0.7183
-1.500 0.0712 0.01544 0.00773 -0.0549 0.8409 0.7372
-1.250 0.0944 0.01550 0.00779 -0.0536 0.8332 0.7539
-1.000 0.1216 0.01548 0.00771 -0.0531 0.8270 0.7677
-0.750 0.1473 0.01546 0.00766 -0.0525 0.8195 0.7768
-0.500 0.1752 0.01540 0.00756 -0.0523 0.8127 0.7853
-0.250 0.2016 0.01538 0.00749 -0.0520 0.8053 0.7950
0.000 0.2287 0.01532 0.00741 -0.0516 0.7982 0.8033
0.250 0.2549 0.01530 0.00737 -0.0512 0.7907 0.8129
0.500 0.2822 0.01524 0.00728 -0.0508 0.7832 0.8227
0.750 0.3078 0.01518 0.00724 -0.0502 0.7738 0.8324
1.000 0.3361 0.01503 0.00706 -0.0498 0.7650 0.8428
1.500 0.3877 0.01480 0.00685 -0.0483 0.7414 0.8655
1.750 0.4146 0.01468 0.00674 -0.0477 0.7291 0.8778
2.000 0.4431 0.01457 0.00666 -0.0475 0.7176 0.8915
2.250 0.4747 0.01446 0.00658 -0.0479 0.7075 0.9060
2.500 0.5077 0.01444 0.00662 -0.0489 0.6953 0.9228
2.750 0.5439 0.01442 0.00666 -0.0505 0.6826 0.9426
3.000 0.5823 0.01439 0.00667 -0.0526 0.6688 0.9671
3.250 0.6186 0.01440 0.00669 -0.0545 0.6540 1.0000
3.500 0.6416 0.01448 0.00677 -0.0537 0.6390 1.0000
3.750 0.6658 0.01457 0.00684 -0.0530 0.6227 1.0000
4.000 0.6904 0.01467 0.00690 -0.0524 0.6049 1.0000
4.250 0.7140 0.01481 0.00705 -0.0516 0.5835 1.0000
4.500 0.7381 0.01496 0.00717 -0.0508 0.5605 1.0000
4.750 0.7615 0.01516 0.00731 -0.0499 0.5333 1.0000
5.000 0.7843 0.01541 0.00747 -0.0489 0.5025 1.0000
5.250 0.8062 0.01574 0.00771 -0.0478 0.4682 1.0000
5.500 0.8271 0.01618 0.00798 -0.0466 0.4324 1.0000
5.750 0.8472 0.01670 0.00833 -0.0453 0.3979 1.0000
6.000 0.8670 0.01726 0.00876 -0.0441 0.3663 1.0000
6.250 0.8866 0.01786 0.00922 -0.0428 0.3376 1.0000
6.500 0.9056 0.01850 0.00975 -0.0416 0.3123 1.0000
6.750 0.9250 0.01912 0.01030 -0.0404 0.2898 1.0000
7.000 0.9438 0.01979 0.01088 -0.0392 0.2702 1.0000
7.250 0.9629 0.02044 0.01149 -0.0381 0.2516 1.0000
7.500 0.9819 0.02106 0.01216 -0.0370 0.2330 1.0000
7.750 1.0004 0.02170 0.01281 -0.0358 0.2148 1.0000
8.000 1.0178 0.02238 0.01348 -0.0344 0.1965 1.0000
8.250 1.0356 0.02304 0.01419 -0.0332 0.1769 1.0000
8.500 1.0509 0.02383 0.01495 -0.0316 0.1556 1.0000
8.750 1.0649 0.02472 0.01579 -0.0300 0.1348 1.0000
9.000 1.0763 0.02573 0.01675 -0.0280 0.1179 1.0000
9.250 1.0867 0.02679 0.01779 -0.0259 0.1059 1.0000
9.500 1.0961 0.02796 0.01895 -0.0237 0.0971 1.0000
9.750 1.1054 0.02918 0.02020 -0.0217 0.0895 1.0000
10.000 1.1147 0.03045 0.02151 -0.0198 0.0835 1.0000
10.250 1.1240 0.03173 0.02287 -0.0181 0.0780 1.0000
10.500 1.1305 0.03326 0.02439 -0.0163 0.0740 1.0000
10.750 1.1412 0.03460 0.02590 -0.0148 0.0704 1.0000
11.000 1.1503 0.03607 0.02752 -0.0134 0.0670 1.0000
11.250 1.1572 0.03768 0.02919 -0.0120 0.0640 1.0000
11.500 1.1647 0.03945 0.03101 -0.0107 0.0614 1.0000
11.750 1.1742 0.04107 0.03284 -0.0095 0.0587 1.0000
12.000 1.1815 0.04283 0.03476 -0.0085 0.0559 1.0000
12.250 1.1862 0.04470 0.03672 -0.0075 0.0532 1.0000
12.500 1.1889 0.04690 0.03891 -0.0067 0.0504 1.0000
12.750 1.1927 0.04904 0.04135 -0.0060 0.0479 1.0000
13.000 1.1935 0.05137 0.04388 -0.0056 0.0448 1.0000
13.250 1.1934 0.05390 0.04654 -0.0054 0.0426 1.0000
13.500 1.1912 0.05675 0.04949 -0.0055 0.0407 1.0000
13.750 1.1886 0.05992 0.05286 -0.0057 0.0386 1.0000
14.000 1.1853 0.06332 0.05653 -0.0061 0.0366 1.0000
14.250 1.1801 0.06703 0.06042 -0.0070 0.0347 1.0000
14.500 1.1731 0.07109 0.06463 -0.0085 0.0329 1.0000
14.750 1.1654 0.07548 0.06913 -0.0101 0.0317 1.0000
15.000 1.1567 0.08024 0.07395 -0.0120 0.0306 1.0000
15.250 1.1452 0.08601 0.08004 -0.0145 0.0294 1.0000
15.500 1.1324 0.09222 0.08649 -0.0175 0.0285 1.0000
15.750 1.1180 0.09903 0.09353 -0.0210 0.0278 1.0000
16.000 1.1016 0.10659 0.10130 -0.0252 0.0271 1.0000
16.250 1.0834 0.11486 0.10976 -0.0299 0.0269 1.0000
16.500 1.0610 0.12457 0.11966 -0.0356 0.0268 1.0000
16.750 1.0318 0.13657 0.13185 -0.0428 0.0273 1.0000
17.000 0.9924 0.15223 0.14760 -0.0520 0.0285 1.0000
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