HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 50,000 Max Cl/Cd: 36.8 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3012-il-50000-n5.txt Download as CSV file: xf-hq3012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3644 0.10422 0.09714 -0.0452 1.0000 0.0530
-9.750 -0.3686 0.10014 0.09316 -0.0465 1.0000 0.0519
-9.500 -0.3750 0.09592 0.08905 -0.0478 1.0000 0.0509
-9.000 -0.4170 0.08319 0.07657 -0.0555 1.0000 0.0471
-8.750 -0.4313 0.07990 0.07340 -0.0553 1.0000 0.0468
-8.500 -0.4505 0.07724 0.07085 -0.0540 1.0000 0.0466
-8.250 -0.4689 0.07451 0.06819 -0.0528 1.0000 0.0464
-8.000 -0.4860 0.07170 0.06540 -0.0514 1.0000 0.0461
-7.750 -0.5022 0.06869 0.06236 -0.0500 1.0000 0.0459
-7.500 -0.5151 0.06551 0.05910 -0.0489 1.0000 0.0458
-7.250 -0.5248 0.06205 0.05550 -0.0480 1.0000 0.0457
-7.000 -0.5304 0.05833 0.05154 -0.0473 1.0000 0.0458
-6.750 -0.5309 0.05463 0.04754 -0.0468 1.0000 0.0459
-6.500 -0.5132 0.04963 0.04193 -0.0497 0.9950 0.0465
-6.250 -0.4894 0.04563 0.03749 -0.0524 0.9891 0.0486
-6.000 -0.4613 0.04330 0.03496 -0.0547 0.9838 0.0522
-5.750 -0.4348 0.04018 0.03128 -0.0563 0.9779 0.0557
-5.500 -0.4031 0.03710 0.02740 -0.0581 0.9730 0.0603
-5.250 -0.3753 0.03534 0.02554 -0.0593 0.9677 0.0661
-5.000 -0.3445 0.03344 0.02306 -0.0601 0.9623 0.0737
-4.750 -0.3122 0.03194 0.02151 -0.0616 0.9579 0.0827
-4.500 -0.2851 0.03073 0.02015 -0.0617 0.9520 0.0922
-4.250 -0.2545 0.02968 0.01884 -0.0621 0.9469 0.1021
-4.000 -0.2218 0.02876 0.01782 -0.0632 0.9425 0.1152
-3.750 -0.1979 0.02792 0.01699 -0.0627 0.9357 0.1251
-3.500 -0.1660 0.02716 0.01618 -0.0640 0.9306 0.1456
-3.000 -0.1097 0.02512 0.01474 -0.0660 0.9188 0.2551
-2.750 -0.0846 0.02408 0.01510 -0.0654 0.9143 0.5281
-2.500 -0.0674 0.02433 0.01541 -0.0627 0.9062 0.6233
-2.250 -0.0416 0.02463 0.01566 -0.0612 0.9006 0.6871
-2.000 -0.0271 0.02490 0.01589 -0.0577 0.8926 0.7374
-1.750 -0.0093 0.02505 0.01607 -0.0540 0.8866 0.7905
-1.500 0.0027 0.02508 0.01609 -0.0498 0.8787 0.8327
-1.250 0.0285 0.02501 0.01592 -0.0485 0.8728 0.8667
-1.000 0.0576 0.02499 0.01576 -0.0487 0.8661 0.8905
-0.750 0.0951 0.02501 0.01562 -0.0508 0.8599 0.9080
-0.500 0.1448 0.02502 0.01544 -0.0552 0.8559 0.9241
-0.250 0.1824 0.02516 0.01546 -0.0580 0.8474 0.9454
0.000 0.2357 0.02516 0.01531 -0.0633 0.8426 0.9672
0.250 0.2677 0.02530 0.01532 -0.0653 0.8334 1.0000
0.500 0.3031 0.02531 0.01520 -0.0673 0.8272 1.0000
0.750 0.3225 0.02557 0.01535 -0.0668 0.8167 1.0000
1.000 0.3566 0.02568 0.01534 -0.0684 0.8099 1.0000
1.250 0.3828 0.02592 0.01549 -0.0688 0.8004 1.0000
1.500 0.4097 0.02617 0.01566 -0.0691 0.7912 1.0000
1.750 0.4449 0.02623 0.01566 -0.0705 0.7841 1.0000
2.000 0.4688 0.02653 0.01592 -0.0703 0.7733 1.0000
2.250 0.5002 0.02661 0.01596 -0.0709 0.7640 1.0000
2.500 0.5345 0.02653 0.01586 -0.0717 0.7548 1.0000
2.750 0.5604 0.02665 0.01597 -0.0713 0.7424 1.0000
3.000 0.5879 0.02671 0.01603 -0.0710 0.7305 1.0000
3.250 0.6184 0.02667 0.01603 -0.0711 0.7198 1.0000
3.500 0.6531 0.02645 0.01583 -0.0717 0.7101 1.0000
3.750 0.6784 0.02655 0.01597 -0.0710 0.6970 1.0000
4.250 0.7319 0.02656 0.01611 -0.0699 0.6699 1.0000
4.500 0.7594 0.02647 0.01608 -0.0693 0.6554 1.0000
4.750 0.7870 0.02634 0.01602 -0.0686 0.6400 1.0000
5.000 0.8151 0.02616 0.01592 -0.0679 0.6236 1.0000
5.250 0.8397 0.02613 0.01596 -0.0668 0.6050 1.0000
5.500 0.8621 0.02620 0.01611 -0.0655 0.5846 1.0000
5.750 0.8896 0.02605 0.01603 -0.0647 0.5646 1.0000
6.000 0.9111 0.02623 0.01627 -0.0633 0.5414 1.0000
6.250 0.9365 0.02626 0.01630 -0.0623 0.5180 1.0000
6.500 0.9596 0.02645 0.01649 -0.0610 0.4927 1.0000
6.750 0.9811 0.02679 0.01685 -0.0597 0.4666 1.0000
7.000 1.0020 0.02723 0.01724 -0.0583 0.4406 1.0000
7.250 1.0222 0.02779 0.01772 -0.0570 0.4156 1.0000
7.500 1.0402 0.02851 0.01840 -0.0554 0.3913 1.0000
7.750 1.0573 0.02933 0.01923 -0.0539 0.3685 1.0000
8.000 1.0740 0.03020 0.02007 -0.0524 0.3472 1.0000
8.250 1.0901 0.03113 0.02099 -0.0509 0.3275 1.0000
8.500 1.1048 0.03213 0.02201 -0.0493 0.3087 1.0000
8.750 1.1194 0.03316 0.02305 -0.0477 0.2912 1.0000
9.000 1.1339 0.03425 0.02415 -0.0461 0.2748 1.0000
9.250 1.1474 0.03539 0.02534 -0.0445 0.2589 1.0000
9.500 1.1601 0.03658 0.02659 -0.0429 0.2438 1.0000
9.750 1.1707 0.03785 0.02792 -0.0411 0.2292 1.0000
10.000 1.1804 0.03919 0.02935 -0.0394 0.2154 1.0000
10.250 1.1883 0.04063 0.03089 -0.0377 0.2021 1.0000
10.500 1.1960 0.04218 0.03255 -0.0360 0.1895 1.0000
10.750 1.2028 0.04383 0.03432 -0.0344 0.1776 1.0000
11.000 1.2089 0.04558 0.03619 -0.0329 0.1665 1.0000
11.250 1.2159 0.04733 0.03798 -0.0315 0.1564 1.0000
11.500 1.2197 0.04937 0.04017 -0.0302 0.1464 1.0000
11.750 1.2232 0.05162 0.04260 -0.0290 0.1371 1.0000
12.000 1.2302 0.05363 0.04461 -0.0279 0.1295 1.0000
12.250 1.2316 0.05630 0.04757 -0.0269 0.1218 1.0000
12.500 1.2348 0.05867 0.04999 -0.0261 0.1153 1.0000
12.750 1.2324 0.06178 0.05339 -0.0254 0.1090 1.0000
13.000 1.2376 0.06404 0.05559 -0.0248 0.1036 1.0000
13.250 1.2312 0.06807 0.06003 -0.0245 0.0992 1.0000
13.500 1.2268 0.07168 0.06384 -0.0245 0.0950 1.0000
13.750 1.2297 0.07432 0.06644 -0.0243 0.0905 1.0000
14.000 1.2135 0.07981 0.07233 -0.0254 0.0879 1.0000
14.250 1.1969 0.08560 0.07842 -0.0270 0.0855 1.0000
14.500 1.1807 0.09159 0.08462 -0.0290 0.0834 1.0000
14.750 1.1675 0.09743 0.09068 -0.0312 0.0814 1.0000
15.000 1.1725 0.10028 0.09352 -0.0315 0.0782 1.0000
15.250 1.1436 0.10957 0.10306 -0.0363 0.0780 1.0000
15.500 1.1102 0.12080 0.11442 -0.0428 0.0782 1.0000
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