HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 200,000 Max Cl/Cd: 71.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3514-il-200000-n5.txt Download as CSV file: xf-hq3514-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3787 0.10920 0.10545 -0.0533 1.0000 0.0204
-12.000 -0.6716 0.04875 0.04454 -0.0847 1.0000 0.0198
-11.750 -0.6676 0.04462 0.04027 -0.0902 0.9911 0.0202
-11.500 -0.6527 0.04194 0.03748 -0.0950 0.9837 0.0206
-11.250 -0.6415 0.03915 0.03452 -0.0990 0.9742 0.0211
-11.000 -0.6290 0.03655 0.03166 -0.1019 0.9649 0.0218
-10.750 -0.6145 0.03372 0.02846 -0.1043 0.9576 0.0231
-10.500 -0.6023 0.03081 0.02505 -0.1054 0.9486 0.0245
-10.250 -0.5788 0.03001 0.02423 -0.1062 0.9420 0.0253
-10.000 -0.5564 0.02916 0.02329 -0.1067 0.9346 0.0264
-9.750 -0.5352 0.02780 0.02169 -0.1070 0.9280 0.0277
-9.500 -0.5162 0.02631 0.01985 -0.1068 0.9200 0.0293
-9.250 -0.4929 0.02531 0.01873 -0.1070 0.9140 0.0307
-9.000 -0.4707 0.02473 0.01810 -0.1067 0.9064 0.0319
-8.750 -0.4451 0.02394 0.01716 -0.1070 0.9012 0.0336
-8.500 -0.4234 0.02305 0.01604 -0.1064 0.8938 0.0354
-8.250 -0.3991 0.02201 0.01480 -0.1063 0.8885 0.0369
-8.000 -0.3748 0.02138 0.01413 -0.1062 0.8828 0.0384
-7.750 -0.3504 0.02084 0.01352 -0.1059 0.8767 0.0401
-7.500 -0.3243 0.02014 0.01267 -0.1058 0.8720 0.0421
-7.250 -0.3003 0.01948 0.01185 -0.1053 0.8656 0.0438
-7.000 -0.2759 0.01876 0.01106 -0.1050 0.8601 0.0457
-6.750 -0.2497 0.01827 0.01052 -0.1050 0.8557 0.0478
-6.500 -0.2257 0.01782 0.01003 -0.1045 0.8490 0.0500
-6.250 -0.2003 0.01732 0.00942 -0.1041 0.8434 0.0524
-6.000 -0.1751 0.01684 0.00884 -0.1038 0.8378 0.0548
-5.750 -0.1509 0.01637 0.00839 -0.1033 0.8310 0.0578
-5.500 -0.1247 0.01599 0.00794 -0.1031 0.8259 0.0611
-5.250 -0.0996 0.01565 0.00754 -0.1028 0.8200 0.0644
-5.000 -0.0744 0.01523 0.00711 -0.1025 0.8147 0.0685
-4.750 -0.0477 0.01491 0.00675 -0.1024 0.8105 0.0733
-4.500 -0.0219 0.01466 0.00643 -0.1021 0.8048 0.0779
-4.250 0.0038 0.01429 0.00606 -0.1019 0.7992 0.0839
-4.000 0.0310 0.01403 0.00573 -0.1019 0.7950 0.0912
-3.750 0.0570 0.01372 0.00543 -0.1017 0.7899 0.0996
-3.500 0.0834 0.01343 0.00514 -0.1016 0.7848 0.1117
-3.000 0.1357 0.01257 0.00465 -0.1016 0.7750 0.2150
-2.750 0.1608 0.01202 0.00443 -0.1016 0.7694 0.3075
-2.500 0.1854 0.01143 0.00443 -0.1013 0.7651 0.4720
-2.250 0.2129 0.01137 0.00439 -0.1011 0.7609 0.5148
-2.000 0.2395 0.01134 0.00440 -0.1008 0.7549 0.5449
-1.750 0.2670 0.01131 0.00437 -0.1005 0.7494 0.5662
-1.500 0.2941 0.01131 0.00437 -0.1002 0.7430 0.5855
-1.250 0.3211 0.01132 0.00438 -0.0999 0.7363 0.6032
-1.000 0.3493 0.01135 0.00435 -0.0997 0.7312 0.6197
-0.750 0.3757 0.01140 0.00442 -0.0993 0.7245 0.6335
-0.500 0.4034 0.01143 0.00441 -0.0992 0.7186 0.6456
-0.250 0.4313 0.01148 0.00441 -0.0991 0.7133 0.6571
0.000 0.4580 0.01151 0.00447 -0.0988 0.7072 0.6651
0.250 0.4861 0.01155 0.00445 -0.0987 0.7015 0.6743
0.750 0.5403 0.01162 0.00450 -0.0983 0.6881 0.6898
1.000 0.5679 0.01165 0.00452 -0.0981 0.6823 0.6960
1.250 0.5944 0.01170 0.00459 -0.0979 0.6747 0.7036
1.500 0.6218 0.01172 0.00460 -0.0977 0.6681 0.7105
1.750 0.6479 0.01177 0.00468 -0.0973 0.6596 0.7184
2.000 0.6749 0.01181 0.00470 -0.0971 0.6519 0.7260
2.250 0.7004 0.01185 0.00479 -0.0966 0.6417 0.7340
2.500 0.7261 0.01189 0.00482 -0.0961 0.6301 0.7416
2.750 0.7514 0.01194 0.00487 -0.0955 0.6170 0.7492
3.000 0.7765 0.01200 0.00491 -0.0949 0.6027 0.7570
3.250 0.8009 0.01207 0.00499 -0.0942 0.5868 0.7650
3.500 0.8251 0.01216 0.00508 -0.0934 0.5686 0.7735
3.750 0.8483 0.01227 0.00517 -0.0925 0.5478 0.7823
4.000 0.8706 0.01243 0.00526 -0.0914 0.5248 0.7913
4.250 0.8919 0.01264 0.00540 -0.0901 0.5006 0.8012
4.500 0.9115 0.01292 0.00557 -0.0886 0.4775 0.8117
4.750 0.9314 0.01322 0.00580 -0.0872 0.4578 0.8235
5.000 0.9520 0.01350 0.00605 -0.0859 0.4426 0.8372
5.250 0.9719 0.01378 0.00633 -0.0845 0.4278 0.8538
5.500 0.9914 0.01404 0.00661 -0.0830 0.4130 0.8777
5.750 1.0175 0.01426 0.00690 -0.0829 0.3959 0.9430
6.000 1.0395 0.01456 0.00720 -0.0821 0.3774 1.0000
6.250 1.0594 0.01495 0.00753 -0.0810 0.3550 1.0000
6.500 1.0761 0.01543 0.00790 -0.0793 0.3340 1.0000
6.750 1.0907 0.01595 0.00830 -0.0773 0.3179 1.0000
7.000 1.1045 0.01650 0.00878 -0.0752 0.3045 1.0000
7.250 1.1196 0.01704 0.00928 -0.0733 0.2928 1.0000
7.500 1.1361 0.01756 0.00979 -0.0717 0.2823 1.0000
7.750 1.1511 0.01814 0.01035 -0.0700 0.2724 1.0000
8.000 1.1676 0.01868 0.01092 -0.0684 0.2617 1.0000
8.250 1.1836 0.01925 0.01150 -0.0669 0.2507 1.0000
8.500 1.1983 0.01988 0.01212 -0.0653 0.2389 1.0000
8.750 1.2126 0.02055 0.01278 -0.0636 0.2264 1.0000
9.000 1.2265 0.02125 0.01348 -0.0620 0.2130 1.0000
9.250 1.2401 0.02200 0.01422 -0.0605 0.2012 1.0000
9.500 1.2524 0.02285 0.01504 -0.0588 0.1905 1.0000
9.750 1.2637 0.02378 0.01594 -0.0571 0.1819 1.0000
10.000 1.2759 0.02470 0.01687 -0.0556 0.1741 1.0000
10.250 1.2867 0.02572 0.01791 -0.0540 0.1681 1.0000
10.500 1.3000 0.02664 0.01888 -0.0527 0.1619 1.0000
10.750 1.3102 0.02776 0.02001 -0.0513 0.1564 1.0000
11.000 1.3227 0.02876 0.02108 -0.0500 0.1512 1.0000
11.250 1.3353 0.02978 0.02217 -0.0489 0.1458 1.0000
11.500 1.3446 0.03103 0.02344 -0.0475 0.1410 1.0000
11.750 1.3573 0.03209 0.02461 -0.0465 0.1364 1.0000
12.000 1.3690 0.03323 0.02584 -0.0455 0.1305 1.0000
12.250 1.3768 0.03467 0.02730 -0.0443 0.1248 1.0000
12.500 1.3888 0.03584 0.02858 -0.0434 0.1169 1.0000
12.750 1.3966 0.03736 0.03013 -0.0424 0.1092 1.0000
13.000 1.4038 0.03897 0.03178 -0.0415 0.0996 1.0000
13.250 1.4104 0.04069 0.03353 -0.0407 0.0886 1.0000
13.500 1.4148 0.04268 0.03553 -0.0398 0.0778 1.0000
13.750 1.4164 0.04499 0.03782 -0.0390 0.0664 1.0000
14.000 1.4158 0.04760 0.04040 -0.0383 0.0564 1.0000
14.250 1.4149 0.05034 0.04316 -0.0377 0.0491 1.0000
14.500 1.4137 0.05322 0.04609 -0.0373 0.0442 1.0000
14.750 1.4117 0.05629 0.04923 -0.0370 0.0403 1.0000
15.000 1.4089 0.05958 0.05260 -0.0369 0.0373 1.0000
15.250 1.4071 0.06286 0.05599 -0.0371 0.0347 1.0000
15.500 1.4025 0.06661 0.05987 -0.0374 0.0324 1.0000
15.750 1.3958 0.07079 0.06414 -0.0381 0.0305 1.0000
16.000 1.3926 0.07463 0.06815 -0.0389 0.0285 1.0000
16.250 1.3861 0.07908 0.07272 -0.0400 0.0267 1.0000
16.500 1.3764 0.08417 0.07793 -0.0415 0.0253 1.0000
16.750 1.3677 0.08928 0.08318 -0.0432 0.0240 1.0000
17.000 1.3605 0.09430 0.08836 -0.0451 0.0227 1.0000
17.250 1.3510 0.09980 0.09402 -0.0472 0.0215 1.0000
17.500 1.3391 0.10582 0.10017 -0.0498 0.0207 1.0000
17.750 1.3261 0.11217 0.10665 -0.0527 0.0201 1.0000
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