HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 200,000 Max Cl/Cd: 80.04 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3514-il-200000.txt Download as CSV file: xf-hq3514-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2581 0.10327 0.10014 -0.0504 0.9916 0.0684
-10.500 -0.2768 0.09596 0.09285 -0.0585 0.9882 0.0721
-10.250 -0.2971 0.08708 0.08399 -0.0679 0.9850 0.0726
-10.000 -0.2696 0.08314 0.08004 -0.0657 0.9836 0.0744
-9.750 -0.2436 0.08107 0.07794 -0.0657 0.9808 0.0770
-9.500 -0.2365 0.07650 0.07336 -0.0688 0.9764 0.0803
-9.250 -0.4620 0.05671 0.05298 -0.0917 0.9705 0.0497
-9.000 -0.4608 0.05120 0.04725 -0.0949 0.9611 0.0488
-8.750 -0.4524 0.04406 0.03961 -0.1002 0.9560 0.0477
-8.500 -0.4486 0.03949 0.03456 -0.1005 0.9459 0.0480
-8.250 -0.4247 0.03536 0.02966 -0.1034 0.9422 0.0502
-8.000 -0.4121 0.03200 0.02590 -0.1029 0.9340 0.0517
-7.750 -0.3811 0.03037 0.02425 -0.1047 0.9302 0.0538
-7.500 -0.3473 0.02899 0.02267 -0.1066 0.9275 0.0571
-7.250 -0.3256 0.02748 0.02080 -0.1061 0.9208 0.0593
-7.000 -0.2997 0.02575 0.01870 -0.1063 0.9157 0.0617
-6.750 -0.2678 0.02426 0.01720 -0.1077 0.9128 0.0648
-6.500 -0.2334 0.02312 0.01592 -0.1091 0.9105 0.0679
-6.250 -0.2148 0.02253 0.01516 -0.1074 0.9018 0.0707
-6.000 -0.1834 0.02127 0.01372 -0.1081 0.8982 0.0740
-5.750 -0.1507 0.02009 0.01256 -0.1091 0.8955 0.0777
-5.500 -0.1306 0.01967 0.01209 -0.1077 0.8875 0.0817
-5.250 -0.1003 0.01918 0.01144 -0.1080 0.8834 0.0859
-5.000 -0.0711 0.01792 0.01027 -0.1083 0.8804 0.0915
-4.750 -0.0503 0.01758 0.00993 -0.1072 0.8732 0.0973
-4.500 -0.0238 0.01686 0.00921 -0.1069 0.8685 0.1041
-4.250 0.0049 0.01624 0.00860 -0.1072 0.8653 0.1129
-4.000 0.0259 0.01582 0.00824 -0.1062 0.8590 0.1233
-3.750 0.0513 0.01533 0.00782 -0.1060 0.8539 0.1397
-3.500 0.0791 0.01464 0.00742 -0.1062 0.8503 0.1987
-3.250 0.0959 0.01342 0.00735 -0.1053 0.8445 0.4622
-3.000 0.1201 0.01341 0.00749 -0.1043 0.8389 0.5484
-2.750 0.1489 0.01343 0.00753 -0.1039 0.8352 0.5892
-2.500 0.1750 0.01358 0.00769 -0.1032 0.8302 0.6157
-2.250 0.1994 0.01377 0.00784 -0.1022 0.8237 0.6371
-2.000 0.2286 0.01381 0.00783 -0.1019 0.8197 0.6532
-1.750 0.2560 0.01391 0.00791 -0.1014 0.8153 0.6671
-1.500 0.2795 0.01406 0.00805 -0.1004 0.8085 0.6796
-1.250 0.3088 0.01401 0.00795 -0.1002 0.8039 0.6920
-1.000 0.3355 0.01407 0.00796 -0.0996 0.7986 0.7048
-0.750 0.3599 0.01413 0.00805 -0.0986 0.7921 0.7160
-0.500 0.3888 0.01405 0.00794 -0.0983 0.7878 0.7266
-0.250 0.4150 0.01409 0.00795 -0.0979 0.7822 0.7367
0.000 0.4407 0.01405 0.00793 -0.0972 0.7760 0.7440
0.250 0.4715 0.01390 0.00771 -0.0975 0.7715 0.7530
0.500 0.4955 0.01390 0.00776 -0.0966 0.7645 0.7598
0.750 0.5244 0.01381 0.00762 -0.0967 0.7587 0.7683
1.000 0.5541 0.01366 0.00746 -0.0967 0.7543 0.7749
1.250 0.5782 0.01370 0.00752 -0.0960 0.7461 0.7842
1.500 0.6072 0.01351 0.00732 -0.0958 0.7403 0.7925
1.750 0.6316 0.01350 0.00734 -0.0951 0.7320 0.8023
2.000 0.6602 0.01335 0.00718 -0.0949 0.7253 0.8119
2.250 0.6846 0.01329 0.00716 -0.0941 0.7164 0.8211
2.500 0.7141 0.01312 0.00694 -0.0941 0.7086 0.8315
2.750 0.7368 0.01302 0.00693 -0.0928 0.6978 0.8417
3.000 0.7626 0.01288 0.00678 -0.0921 0.6880 0.8529
3.250 0.7882 0.01272 0.00664 -0.0913 0.6776 0.8655
3.500 0.8103 0.01262 0.00660 -0.0900 0.6655 0.8797
3.750 0.8330 0.01249 0.00651 -0.0887 0.6530 0.8956
4.000 0.8572 0.01236 0.00641 -0.0877 0.6407 0.9148
4.250 0.8864 0.01224 0.00634 -0.0878 0.6261 0.9427
4.500 0.9243 0.01219 0.00631 -0.0900 0.6076 1.0000
4.750 0.9515 0.01229 0.00636 -0.0903 0.5905 1.0000
5.000 0.9775 0.01241 0.00643 -0.0902 0.5717 1.0000
5.500 1.0253 0.01281 0.00666 -0.0891 0.5283 1.0000
6.000 1.0684 0.01349 0.00709 -0.0871 0.4833 1.0000
6.250 1.0885 0.01395 0.00740 -0.0858 0.4619 1.0000
6.500 1.1080 0.01447 0.00778 -0.0845 0.4414 1.0000
6.750 1.1267 0.01497 0.00822 -0.0831 0.4210 1.0000
7.000 1.1448 0.01546 0.00865 -0.0816 0.4013 1.0000
7.250 1.1618 0.01593 0.00908 -0.0799 0.3819 1.0000
7.500 1.1773 0.01638 0.00950 -0.0780 0.3621 1.0000
7.750 1.1900 0.01687 0.00994 -0.0756 0.3427 1.0000
8.000 1.2002 0.01751 0.01047 -0.0728 0.3250 1.0000
8.250 1.2105 0.01827 0.01112 -0.0702 0.3083 1.0000
8.500 1.2220 0.01909 0.01185 -0.0679 0.2924 1.0000
8.750 1.2344 0.01990 0.01261 -0.0658 0.2773 1.0000
9.000 1.2472 0.02071 0.01339 -0.0639 0.2635 1.0000
9.250 1.2598 0.02151 0.01415 -0.0620 0.2509 1.0000
9.500 1.2717 0.02233 0.01491 -0.0601 0.2396 1.0000
9.750 1.2842 0.02304 0.01568 -0.0583 0.2286 1.0000
10.000 1.2974 0.02383 0.01651 -0.0566 0.2193 1.0000
10.250 1.3092 0.02472 0.01735 -0.0549 0.2112 1.0000
10.500 1.3226 0.02552 0.01824 -0.0535 0.2029 1.0000
10.750 1.3337 0.02653 0.01918 -0.0519 0.1957 1.0000
11.000 1.3467 0.02741 0.02018 -0.0505 0.1885 1.0000
11.250 1.3583 0.02850 0.02121 -0.0491 0.1822 1.0000
11.500 1.3709 0.02947 0.02232 -0.0478 0.1760 1.0000
11.750 1.3813 0.03061 0.02346 -0.0464 0.1697 1.0000
12.000 1.3911 0.03179 0.02472 -0.0451 0.1627 1.0000
12.250 1.3981 0.03312 0.02607 -0.0436 0.1553 1.0000
12.500 1.4054 0.03447 0.02753 -0.0423 0.1479 1.0000
12.750 1.4108 0.03598 0.02909 -0.0410 0.1406 1.0000
13.000 1.4176 0.03746 0.03072 -0.0399 0.1331 1.0000
13.250 1.4208 0.03926 0.03254 -0.0388 0.1255 1.0000
13.500 1.4267 0.04093 0.03438 -0.0380 0.1155 1.0000
13.750 1.4298 0.04295 0.03648 -0.0372 0.1042 1.0000
14.000 1.4301 0.04538 0.03892 -0.0364 0.0908 1.0000
14.250 1.4262 0.04834 0.04184 -0.0357 0.0775 1.0000
14.500 1.4203 0.05166 0.04514 -0.0352 0.0669 1.0000
14.750 1.4137 0.05523 0.04873 -0.0348 0.0592 1.0000
15.000 1.4038 0.05931 0.05281 -0.0347 0.0543 1.0000
15.250 1.3973 0.06319 0.05679 -0.0348 0.0493 1.0000
15.500 1.3836 0.06812 0.06174 -0.0354 0.0461 1.0000
15.750 1.3776 0.07227 0.06604 -0.0360 0.0427 1.0000
16.000 1.3673 0.07713 0.07098 -0.0371 0.0401 1.0000
16.250 1.3538 0.08254 0.07640 -0.0384 0.0379 1.0000
16.500 1.3482 0.08706 0.08109 -0.0396 0.0358 1.0000
16.750 1.3416 0.09177 0.08589 -0.0410 0.0340 1.0000
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