HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 100,000 Max Cl/Cd: 55.77 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3514-il-100000.txt Download as CSV file: xf-hq3514-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4010 0.10151 0.09719 -0.0327 1.0000 0.1416
-8.750 -0.4394 0.10024 0.09606 -0.0321 1.0000 0.1446
-8.500 -0.4868 0.09887 0.09484 -0.0316 1.0000 0.1454
-8.250 -0.4520 0.09586 0.09180 -0.0270 1.0000 0.1504
-8.000 -0.4629 0.09441 0.09040 -0.0246 1.0000 0.1553
-7.750 -0.5323 0.08554 0.08151 -0.0459 0.9859 0.1610
-7.500 -0.4685 0.08714 0.08319 -0.0319 0.9886 0.1724
-7.250 -0.4578 0.08332 0.07937 -0.0347 0.9835 0.1827
-7.000 -0.4726 0.07659 0.07263 -0.0447 0.9736 0.1945
-6.750 -0.5120 0.05084 0.04505 -0.0651 0.9625 0.1025
-6.500 -0.4884 0.04642 0.04031 -0.0666 0.9588 0.0964
-6.250 -0.4600 0.04239 0.03569 -0.0692 0.9556 0.0962
-6.000 -0.4434 0.03973 0.03258 -0.0686 0.9501 0.0968
-5.750 -0.4160 0.03715 0.02948 -0.0696 0.9459 0.0976
-5.500 -0.3828 0.03583 0.02752 -0.0711 0.9425 0.1008
-5.250 -0.3555 0.03330 0.02480 -0.0719 0.9395 0.1036
-5.000 -0.3346 0.03218 0.02359 -0.0713 0.9347 0.1073
-4.750 -0.3037 0.03121 0.02239 -0.0721 0.9302 0.1128
-4.500 -0.2656 0.03002 0.02096 -0.0740 0.9267 0.1175
-4.250 -0.2445 0.02923 0.02024 -0.0733 0.9212 0.1238
-4.000 -0.2135 0.02859 0.01944 -0.0739 0.9153 0.1314
-3.750 -0.1715 0.02773 0.01874 -0.0765 0.9110 0.1434
-3.500 -0.1529 0.02726 0.01838 -0.0752 0.9028 0.1535
-3.250 -0.1141 0.02673 0.01795 -0.0771 0.8973 0.1735
-3.000 -0.0896 0.02626 0.01765 -0.0769 0.8905 0.2010
-2.750 -0.0655 0.02456 0.01720 -0.0774 0.8853 0.3738
-2.500 -0.0393 0.02493 0.01831 -0.0755 0.8810 0.6245
-2.250 -0.0282 0.02561 0.01899 -0.0719 0.8740 0.6628
-2.000 -0.0049 0.02615 0.01949 -0.0703 0.8683 0.6951
-1.750 0.0284 0.02661 0.01990 -0.0699 0.8644 0.7260
-1.500 0.0336 0.02704 0.02032 -0.0658 0.8554 0.7448
-1.250 0.0652 0.02726 0.02046 -0.0656 0.8503 0.7684
-1.000 0.0768 0.02758 0.02078 -0.0624 0.8421 0.7858
-0.750 0.1003 0.02770 0.02089 -0.0607 0.8360 0.8063
-0.500 0.1181 0.02789 0.02107 -0.0584 0.8292 0.8270
-0.250 0.1354 0.02799 0.02115 -0.0562 0.8215 0.8472
0.000 0.1690 0.02781 0.02095 -0.0560 0.8175 0.8661
0.250 0.1785 0.02798 0.02111 -0.0532 0.8062 0.8811
0.500 0.2250 0.02755 0.02061 -0.0555 0.8018 0.8953
0.750 0.2416 0.02756 0.02062 -0.0538 0.7896 0.9117
1.000 0.2957 0.02693 0.01993 -0.0572 0.7856 0.9261
1.250 0.3255 0.02704 0.02006 -0.0582 0.7739 0.9437
1.500 0.3906 0.02638 0.01935 -0.0640 0.7711 0.9553
1.750 0.4363 0.02649 0.01946 -0.0682 0.7598 0.9734
2.000 0.5062 0.02555 0.01849 -0.0747 0.7568 0.9845
2.250 0.5311 0.02562 0.01853 -0.0754 0.7453 1.0000
2.500 0.5788 0.02491 0.01779 -0.0785 0.7413 1.0000
2.750 0.6011 0.02507 0.01793 -0.0784 0.7298 1.0000
3.000 0.6510 0.02424 0.01706 -0.0814 0.7257 1.0000
3.250 0.6773 0.02433 0.01715 -0.0816 0.7143 1.0000
3.500 0.7256 0.02350 0.01630 -0.0843 0.7096 1.0000
3.750 0.7523 0.02354 0.01634 -0.0843 0.6979 1.0000
4.000 0.8045 0.02233 0.01511 -0.0870 0.6926 1.0000
4.250 0.8332 0.02203 0.01480 -0.0868 0.6791 1.0000
4.500 0.8646 0.02159 0.01435 -0.0868 0.6658 1.0000
4.750 0.8974 0.02110 0.01385 -0.0869 0.6526 1.0000
5.000 0.9301 0.02064 0.01337 -0.0871 0.6388 1.0000
5.250 0.9609 0.02030 0.01302 -0.0870 0.6243 1.0000
5.500 0.9892 0.02008 0.01279 -0.0866 0.6084 1.0000
5.750 1.0154 0.01994 0.01264 -0.0859 0.5909 1.0000
6.000 1.0416 0.01982 0.01250 -0.0852 0.5721 1.0000
6.250 1.0691 0.01970 0.01231 -0.0846 0.5525 1.0000
6.500 1.0902 0.01985 0.01243 -0.0832 0.5299 1.0000
6.750 1.1144 0.02000 0.01245 -0.0823 0.5073 1.0000
7.000 1.1360 0.02037 0.01272 -0.0811 0.4840 1.0000
7.250 1.1591 0.02086 0.01305 -0.0802 0.4616 1.0000
7.500 1.1806 0.02151 0.01357 -0.0792 0.4394 1.0000
7.750 1.1992 0.02222 0.01423 -0.0777 0.4173 1.0000
8.000 1.2181 0.02293 0.01482 -0.0764 0.3962 1.0000
8.250 1.2321 0.02364 0.01552 -0.0743 0.3755 1.0000
8.500 1.2459 0.02434 0.01620 -0.0721 0.3560 1.0000
8.750 1.2616 0.02509 0.01688 -0.0704 0.3382 1.0000
9.000 1.2801 0.02599 0.01765 -0.0691 0.3217 1.0000
9.250 1.3009 0.02705 0.01860 -0.0684 0.3064 1.0000
9.500 1.3226 0.02820 0.01975 -0.0678 0.2933 1.0000
9.750 1.3458 0.02939 0.02094 -0.0675 0.2818 1.0000
10.000 1.3711 0.03051 0.02196 -0.0675 0.2705 1.0000
10.250 1.3821 0.03144 0.02306 -0.0653 0.2604 1.0000
10.500 1.3957 0.03239 0.02408 -0.0635 0.2505 1.0000
10.750 1.4126 0.03316 0.02474 -0.0623 0.2401 1.0000
11.000 1.4110 0.03400 0.02585 -0.0583 0.2320 1.0000
11.250 1.4262 0.03486 0.02669 -0.0569 0.2238 1.0000
11.500 1.4293 0.03586 0.02790 -0.0539 0.2163 1.0000
11.750 1.4413 0.03681 0.02884 -0.0522 0.2086 1.0000
12.000 1.4434 0.03792 0.03014 -0.0494 0.2011 1.0000
12.250 1.4507 0.03903 0.03129 -0.0474 0.1933 1.0000
12.500 1.4524 0.04024 0.03261 -0.0450 0.1851 1.0000
12.750 1.4531 0.04175 0.03425 -0.0426 0.1767 1.0000
13.000 1.4584 0.04309 0.03547 -0.0409 0.1666 1.0000
13.250 1.4477 0.04512 0.03775 -0.0381 0.1581 1.0000
13.500 1.4418 0.04721 0.03991 -0.0360 0.1482 1.0000
13.750 1.4376 0.04927 0.04190 -0.0343 0.1377 1.0000
14.000 1.4230 0.05213 0.04500 -0.0325 0.1287 1.0000
14.250 1.4120 0.05512 0.04809 -0.0312 0.1194 1.0000
14.500 1.4044 0.05792 0.05081 -0.0303 0.1106 1.0000
14.750 1.3909 0.06165 0.05477 -0.0298 0.1027 1.0000
15.000 1.3827 0.06515 0.05831 -0.0295 0.0956 1.0000
15.250 1.3736 0.06889 0.06213 -0.0296 0.0889 1.0000
15.500 1.3653 0.07294 0.06631 -0.0299 0.0829 1.0000
15.750 1.3577 0.07695 0.07037 -0.0305 0.0776 1.0000
16.000 1.3509 0.08117 0.07467 -0.0311 0.0726 1.0000
16.250 1.3424 0.08573 0.07936 -0.0322 0.0683 1.0000
16.500 1.3412 0.08926 0.08279 -0.0327 0.0638 1.0000
16.750 1.3294 0.09474 0.08857 -0.0344 0.0611 1.0000
17.000 1.3233 0.09935 0.09331 -0.0358 0.0582 1.0000
17.250 1.3318 0.10162 0.09541 -0.0355 0.0545 1.0000
17.500 1.3178 0.10783 0.10194 -0.0381 0.0534 1.0000
17.750 1.3028 0.11439 0.10876 -0.0411 0.0523 1.0000
18.000 1.2867 0.12135 0.11598 -0.0446 0.0515 1.0000
18.250 1.2675 0.12919 0.12406 -0.0490 0.0510 1.0000
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